Rocket body structure capable of realizing long-term on-orbit power supply

Abstract

The invention discloses a rocket body structure capable of achieving long-term on-orbit power supply. The rocket body structure comprises a main force bearing structure, a separation device, a connector and a solar cell substrate. Wherein the separating device and the connecting joint are respectively arranged on the main force bearing structure; the main force bearing structure is connected with the solar cell substrate capable of supplying power through the connector so that the function that the solar cell substrate supplies power to the rocket body structure can be achieved. The main force bearing structure is connected with the adjacent structure through the separation device so as to achieve the structure separation function. The problems that the residual value of the tail sub-stage of an existing carrier rocket is difficult to utilize, and track resources are occupied are solved.

Description

Technical Field

[0001] The invention belongs to the technical field of launch vehicle body structure design, and in particular relates to a body structure capable of providing power on-orbit for a long time. Background Art

[0002] In order to improve the rocket's carrying capacity, most of the current domestic and foreign launch vehicle models adopt a multi-stage series or parallel configuration. After performing a satellite launch mission, the rocket's final stage often has no active deorbiting capability or has a poor deorbiting capability, resulting in the final stage remaining in a high flight orbit in space for a long time, wasting its residual value and occupying a large amount of space orbital resources.

[0003] For the current domestic and foreign launch vehicle terminal stage rocket body structure, it has two main functions: first, before separation from the payload, the structure bears and transmits a large flight load, while meeting the installation requirements of various system instruments and equipment to ensure reliable and firm connection; second, the rocket body structure must ensure reliable unlocking according to the control system requirements to achieve successful separation of the terminal stage from the payload. According to its use requirements, on the one hand, the rocket body structure is developed only considering the load-bearing and environmental use requirements and the lightweight requirements to improve the carrying efficiency, and does not have the ability to supply power on orbit, and cannot meet the long-term orbital requirements of the terminal stage; on the other hand, the rocket body structure faces a complex and harsh high and low temperature cycle environment for a long time when it stays in orbit, which also puts forward extremely high requirements on the durability and thermal deformation matching of the local structure, but this consideration is often not taken into account in the existing structural design.

[0004] With the development of aerospace technology, in order to further support the expansion of launch vehicles in the space field, fully explore the residual value of the rocket's final stage after completing its target mission, actively explore a new model of long-term on-orbit, low-cost space equipment identification, and provide solutions for on-orbit assessment of space application payloads and acquisition of space target characteristic data. In response to this demand, the launch vehicle's final stage body structure, in addition to the conventional load-bearing and separation requirements, must also have the ability to remain in orbit for a long time and be used for a long time in a high and low temperature cycle environment. Therefore, it is urgent to develop a body structure design technology that can provide long-term on-orbit power supply, laying a solid foundation for the future development of the space-based field. Summary of the invention

[0005] The technology of the present invention solves the problem: overcome the shortcomings of the prior art and provide a rocket body structure that can provide power in orbit for a long time, so as to solve the problems that the residual value of the last stage of the existing launch vehicle is difficult to utilize and occupies orbital resources.

[0006] In order to solve the above technical problems, the present invention discloses a rocket body structure that can provide power in orbit for a long time, comprising: a main load-bearing structure, a separation device, a connecting joint and a solar cell substrate; wherein the separation device and the connecting joint are respectively installed on the main load-bearing structure; the main load-bearing structure is connected to the power-supplying solar cell substrate through the connecting joint to realize the power supply function of the solar cell substrate to the rocket body structure; the main load-bearing structure is connected to the adjacent structure through the separation device to realize the structural separation function.

[0007] In the above-mentioned rocket body structure that can provide long-term in-orbit power supply, the main load-bearing structure is used to realize the load-bearing function and is a circular ring structure.

[0008] In the above-mentioned rocket body structure capable of long-term on-orbit power supply, the separation device is connected to the inner side surface of the main load-bearing structure, and the connecting joint is connected to the outer side surface of the main load-bearing structure.

[0009] In the above-mentioned rocket body structure capable of long-term on-orbit power supply, the connecting joint is an L-shaped structure.

[0010] In the above-mentioned rocket body structure that can provide power in orbit for a long time, one side of the L-shaped structure is connected to the solar cell substrate through bolts A, spring washers, heat-proof bushings and self-locking nuts A to prevent heat and loosening; wherein, bolt A passes through one side of the L-shaped structure and the solar cell substrate and is connected to the self-locking nut A, and the spring washers and heat-proof bushings are installed between the self-locking nut A and the solar cell substrate.

[0011] In the above-mentioned rocket body structure capable of long-term on-orbit power supply, connection holes for installing bolts A are opened on one side of the L-shaped structure and on the solar cell substrate, and the connection holes are oblong holes.

[0012] In the above-mentioned rocket body structure that can provide long-term on-orbit power supply, the other side of the L-shaped structure is connected to the main load-bearing structure and prevented from loosening by bolts B and self-locking nuts B; wherein, bolt B passes through the other side of the L-shaped structure and the main load-bearing structure and is connected to the self-locking nut B.

[0013] In the above-mentioned rocket body structure that can provide long-term in-orbit power supply, the main load-bearing structure, connecting joints and solar cell substrates are all made of composite materials or sandwich structures.

[0014] The present invention has the following advantages:

[0015] (1) The present invention discloses a rocket body structure that can provide power for a long time in orbit. Based on the requirement of long-term in-orbit operation of the rocket body structure, a main load-bearing structure + solar cell substrate combined design is proposed, which solves the problem of compact space layout while realizing the load-bearing and separation functions.

[0016] (2) The present invention discloses a rocket body structure capable of long-term on-orbit power supply. Within the space envelope limited by the fairing, the main load-bearing structure and the solar cell substrate are radially connected through a connecting joint to form a whole. The structural layout is neat, uniform, and compact, which greatly improves the overall and local stiffness of the structure. At the same time, the radial connection method does not affect the axial load and separation of the main load-bearing structure, avoids the transfer of load to the solar cell substrate, and causes local large deformation or failure of the substrate structure, thereby ensuring effective load bearing of the structure.

[0017] (3) The present invention discloses a rocket body structure that can provide power on orbit for a long time. The solar cell substrate is connected to the main load-bearing structure through a connecting joint, and both are designed as high-temperature resistant composite materials or sandwich structures, which improves the thermal deformation matching between structures in the space environment and achieves the overall stiffness and strength index requirements. In the long-term orbital operation space environment, when the rocket body structure faces a complex and harsh high and low temperature cycle environment, this design scheme significantly improves the thermal deformation matching between the various components of the structure, avoids large thermal stress inside the structure that causes large deformation or damage to the solar cell substrate, and ensures the effective power supply capacity of the structure.

[0018] (4) The present invention discloses a rocket body structure that can provide power for a long time in orbit. The solar cell substrate adopts a carbon panel aluminum honeycomb sandwich structure, which has the advantages of light weight and high efficiency in load-bearing performance, can significantly improve the load-bearing efficiency of the rocket body structure, and at the same time can ensure that the structure has sufficient rigidity to ensure the power supply reliability of the solar cells; at the same time, the solar cell substrate and the main load-bearing structure adopt a post-assembly method, and for launch missions that do not require long-term orbital power supply, the connection joints and the solar cell substrate can be directly removed, which greatly improves the applicability of the structure and can meet the use and modification requirements of multiple missions at the same time.

[0019] (5) The present invention discloses a rocket body structure that can provide power for a long time in orbit. The structure has been successfully applied, so that the rocket body structure of the final stage of the carrier rocket has, in addition to the conventional bearing and separation functions, the additional capabilities of long-term on-orbit power supply and long-term use in high and low temperature cycle environments, thereby improving product adaptability and rocket launch efficiency, and having significant economic value.

[0020] (6) The present invention discloses a rocket body structure that can provide power in orbit for a long time. The structure can be widely used in the field of launch vehicle design. It has important scientific and technological value for further supporting the expansion of launch vehicles in the space field and fully exploring the remaining capacity of the rocket's last stage after completing its target mission. It can also lay a solid foundation for the future development of the space-based field. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 1 is a schematic structural diagram of a rocket body structure capable of long-term on-orbit power supply in an embodiment of the present invention;

[0022] Figure 2It is a schematic diagram of the connection between a main load-bearing structure, a connecting joint and a solar cell substrate in an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0024] One of the core ideas of the present invention is that based on the limitations of the cylindrical rocket body shell structure and its internal space, a rocket body structure that can provide long-term on-orbit power supply is proposed, while meeting the load-bearing function and long-term on-orbit power supply function, aiming to solve the problems that the surplus value of the last stage of the existing launch vehicle is difficult to utilize and occupies orbital resources.

[0025] Reference Figure 1 In this embodiment, the rocket body structure capable of long-term on-orbit power supply comprises: a main load-bearing structure 1, a separation device 2, a connection joint 3 and a solar cell substrate 4. The main load-bearing structure 1 is used to realize the bearing function and is a ring structure; the separation device 2 and the connection joint 3 are respectively installed on the main load-bearing structure 1; the main load-bearing structure 1 is connected to the solar cell substrate 4 capable of power supply through the connection joint 3 to realize the power supply function of the solar cell substrate 4 to the rocket body structure; the main load-bearing structure 1 is connected to the adjacent structure through the separation device 2 to realize the structure separation function.

[0026] In this embodiment, the separation device 2 is connected to the inner side of the main load-bearing structure 1, and the connection joint 3 is connected to the outer side of the main load-bearing structure 1. Figure 2 As shown, the connection joint 3 is an L-shaped structure. Among them, one side of the L-shaped structure is connected to the solar cell substrate 4 through bolts A81, spring washers 6, heat-proof bushings 7 and self-locking nuts A51 to prevent heat and loosening: bolt A81 passes through one side of the L-shaped structure and the solar cell substrate 4 and is connected to the self-locking nut A51, and spring washers 6 and heat-proof bushings 7 are installed between the self-locking nut A51 and the solar cell substrate 4. The other side of the L-shaped structure is connected to the main load-bearing structure 1 through bolts B82 and self-locking nuts B52 to prevent loosening: bolts B82 pass through the other side of the L-shaped structure and the main load-bearing structure 1 and are connected to the self-locking nut B52. Furthermore, one side of the L-shaped structure and the solar cell substrate 4 are provided with connection holes for installing bolts A81, and the connection holes are oblong holes.

[0027] In this embodiment, the main load-bearing structure 1, the connection joint 3 and the solar cell substrate 4 are all made of composite materials or sandwich structures that can withstand high and low temperature alternating environments for a long time.

[0028] In summary, under the above connection method, the load on the structure during the flight of the rocket body is borne by the main load-bearing structure and transmitted to the upstream and downstream structures, meeting the load-bearing requirements of the structural system; the power-supplying solar cell substrate is reliably connected to the main load-bearing structure, and the circuit system can realize the power supply of various systems on the rocket by the rocket body structure under long-term orbit conditions, meeting the power supply requirements of the structural system; the main load-bearing structure, the connecting joint and the solar cell substrate are all made of composite materials or sandwich structures that can withstand high and low temperature alternating environments for a long time, and the connecting holes on the connecting joint and the solar cell substrate are opened as oblong holes, so that the structure has deformation coordination adaptability under high and low temperature environments, meeting the structural adaptability requirements of long-term orbital environments; the main load-bearing structure is connected to the adjacent structure through a separation device, meeting the separation requirements of the structural system during flight.

[0029] Based on the above embodiment, a specific example is described below.

[0030] like Figure 1 As shown, the main load-bearing structure 1 is made of T700-grade carbon fiber epoxy resin-based composite material (which can meet long-term high-temperature environmental conditions), the upper end face is connected to the remaining sections using 90 M5 butt bolts, and the inner side of the lower end face uses an aluminum alloy separation device 2 and is installed with 6 explosive bolts to achieve connection and separation with the remaining sections.

[0031] Furthermore, the connection joint 3 is made of T700 grade carbon fiber epoxy resin-based composite material, which is consistent with the material of the main load-bearing structure 1, thereby improving the matching of the thermal deformation of the structure; at the same time, the connection joint 3 and the side wall of the main load-bearing structure 1 are connected and prevented from loosening by using 10 M5 bolts and self-locking nuts, which are evenly distributed at 8 locations in the circumferential direction;

[0032] Furthermore, the solar cell substrate 4 that can supply power adopts a T800-grade carbon panel + aluminum honeycomb sandwich structure, which is designed as an isosceles trapezoidal structure and is evenly distributed at 8 locations in the circumferential direction. The two oblique sides are connected to the connection joints 3 using 11 M5 bolts, self-locking nuts, spring washers and heat-proof bushings to achieve connection, heat protection and loosening prevention.

[0033] The rocket body structure design that can provide long-term on-orbit power supply has been verified through model ground static tests, high and low temperature cycle tests and vacuum pressure drop tests, and can meet both the load-bearing function requirements and the long-term on-orbit power supply requirements.

[0034] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0035] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A rocket body structure capable of long-term on-orbit power supply, characterized in that: include: A main load-bearing structure (1), a separation device (2), a connection joint (3) and a solar cell substrate (4); wherein the separation device (2) and the connection joint (3) are respectively installed on the main load-bearing structure (1); the main load-bearing structure (1) is connected to a solar cell substrate (4) capable of supplying power via the connection joint (3) to realize the function of the solar cell substrate (4) supplying power to the rocket body structure; and the main load-bearing structure (1) is connected to an adjacent structure via the separation device (2) to realize the function of structural separation.

2. The rocket body structure capable of long-term on-orbit power supply according to claim 1, characterized in that: The main load-bearing structure (1) is used to realize the load-bearing function and is a circular ring structure.

3. The rocket body structure capable of long-term on-orbit power supply according to claim 1 or 2, characterized in that: The separation device (2) is connected to the inner side surface of the main load-bearing structure (1), and the connection joint (3) is connected to the outer side surface of the main load-bearing structure (1).

4. The rocket body structure capable of long-term on-orbit power supply according to claim 1, characterized in that: The connecting joint (3) is an L-shaped structure.

5. The rocket body structure capable of long-term on-orbit power supply according to claim 4, characterized in that: A side surface of the L-shaped structure is connected to a solar cell substrate (4) via a bolt A (81), a spring washer (6), a heat-proof bushing (7) and a self-locking nut A (51) to prevent heat and loosening; wherein the bolt A (81) passes through a side surface of the L-shaped structure and the solar cell substrate (4) and is connected to the self-locking nut A (51), and the spring washer (6) and the heat-proof bushing (7) are installed between the self-locking nut A (51) and the solar cell substrate (4).

6. The rocket body structure capable of long-term on-orbit power supply according to claim 5, characterized in that: A connection hole for installing a bolt A (81) is provided on one side of the L-shaped structure and on the solar cell substrate (4), and the connection hole is an oblong hole.

7. The rocket body structure capable of long-term on-orbit power supply according to claim 4, characterized in that: The other side of the L-shaped structure is connected to the main load-bearing structure (1) through a bolt B (82) and a self-locking nut B (52) to prevent loosening; wherein the bolt B (82) passes through the other side of the L-shaped structure and the main load-bearing structure (1) and is connected to the self-locking nut B (52).

8. The rocket body structure capable of long-term on-orbit power supply according to claim 1, characterized in that: The main load-bearing structure (1), the connecting joint (3) and the solar cell substrate (4) all adopt composite materials or sandwich structures.

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