Extensible universal liquid upper-level spacecraft

Abstract

The utility model relates to the field of space flight and aviation, in particular to an extensible universal liquid upper-stage spacecraft which comprises an upper-stage body, an extension section, an instrument mounting table, a support, a flight control system, an avionics system and a power system. The upper edge of the upper-stage main body is provided with a butt joint interface, the lower edge of the upper-stage main body is in butt joint and fixed with the upper edge of the extension section, and the lower edge of the extension section is provided with a butt joint interface; the instrument mounting table is fixed in the upper stage main body; the flight control system and the avionics system are mounted on the instrument mounting table; the support is fixed in the upper stage body and located below the instrument mounting table, and the engine system is detachably connected to the middle position of the support; all the storage boxes are uniformly and detachably connected to the bracket and are symmetrically distributed; all tanks are in communication with an engine system. The universality of the upper stage can be improved, and the extensible range of the upper stage is enlarged, so that the development cost is reduced, the development time is shortened, and the technical risk is reduced.

Description

Technical Field

[0001] This application relates to the field of aerospace, and more particularly to a scalable, general-purpose liquid upper stage spacecraft. Background Technology

[0002] The upper stage is an important component of the space transportation system. It refers to a rocket substage added to the basic rocket stage, which has an independent control and propulsion system. It is an autonomous and independent spacecraft that can further send payloads from quasi-Earth orbit or Earth orbit into a predetermined working orbit or predetermined space location. It generally has the characteristics of multiple restarts, long-term on-orbit operation, autonomous flight, and multi-mission adaptability. It can complete tasks such as orbit transfer and orbit deployment, and is an effective way to improve rocket performance and mission adaptability.

[0003] With the development of aerospace technology, there are more and more types of space payloads and different working orbits. In order to meet the orbital requirements, an upper stage is added to the rocket to increase the rocket's flexibility and enter more types of orbits. In addition, for the same orbit, the upper stage increases the rocket's carrying capacity and further improves the profitability of a single rocket.

[0004] However, existing upper stages are generally developed using a customized approach. A single upper stage has limited adaptability to different missions and poor scalability. When missions differ significantly, a new upper stage configuration must be developed, leading to high development costs, long development times, and numerous technical risks. For example, the existing YZ1 series upper stages in China are designed for fixed missions and are difficult to expand significantly, resulting in limited compatibility with rockets and missions, and they are basically used in conjunction with fixed rockets.

[0005] Therefore, how to improve the versatility and expand the scalability of the upper level, thereby reducing development costs and time, and reducing technical risks, is a technical problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0006] This application provides a scalable and versatile liquid upper stage spacecraft to improve the versatility of the upper stage, increase its scalability, thereby reducing development costs and time, and mitigating technological risks.

[0007] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0008] A scalable and universal liquid upper stage spacecraft includes: an upper stage body, an extension section, an instrument mounting platform, and a support frame, as well as interconnected flight control, avionics, and propulsion systems. The upper stage body has a docking interface at its upper edge for docking and fixing with the lower edge of the extension section of another liquid upper stage spacecraft used for expansion. The lower edge of the upper stage body docks and is fixed with the upper edge of the extension section. The lower edge of the extension section has a docking interface for docking and fixing with the final stage of a rocket. The instrument mounting platform is fixed inside the upper stage body, and instruments from the flight control system and avionics system are mounted on the instrument mounting platform. The support frame is fixed inside the upper stage body and located below the instrument mounting platform. The engine system of the propulsion system is detachably connected to the middle position of the support frame. All tanks of the propulsion system are uniformly and detachably connected to the support frame, and groups of two tanks are symmetrically distributed about the central axis of the support frame. All tanks of the propulsion system are connected to the engine system.

[0009] In the scalable, general-purpose liquid upper stage spacecraft described above, preferably, the diameter of the upper stage body and extension is 3.2m, and the total height of the upper stage body and extension is 3.2m.

[0010] In the scalable, general-purpose liquid upper stage spacecraft described above, preferably, the lower edge of the upper stage body abuts against the upper edge of the extension and is fixedly connected by explosive bolts and a release spring.

[0011] In the scalable, general-purpose liquid upper stage spacecraft described above, preferably, the inner side of the docking interface at the upper edge of the upper stage body is lower than the outer side, and the inner side of the docking interface at the lower edge of the extension is higher than the outer side.

[0012] The scalable, general-purpose liquid upper stage spacecraft described above preferably includes a propulsion system comprising: one 20kN extrusion main engine and twelve 25N nozzles.

[0013] The scalable, general-purpose liquid upper stage spacecraft described above preferably has a propulsion system with four tanks, which are divided into two groups, and the two groups of tanks are symmetrically and uniformly detachably connected to a support.

[0014] The scalable, general-purpose liquid upper stage spacecraft described above preferably includes a propulsion system with three gas cylinders connected to tanks for pressurizing tanks storing oxidizer and fuel.

[0015] The scalable general-purpose liquid upper stage spacecraft described above preferably has a mass of 5.1t and a takeoff thrust of 20kN after the tanks are filled with propellant.

[0016] The scalable, general-purpose liquid upper stage spacecraft described above preferably includes multiple tanks of a propulsion system mounted on a support frame within the scalable liquid upper stage spacecraft; and all tanks within the liquid upper stage spacecraft belong to the propulsion system of the lower liquid upper stage spacecraft and are connected to the engine system of the lower liquid upper stage spacecraft.

[0017] Compared to the aforementioned background technologies, the scalable and universal liquid upper stage spacecraft of this application can improve the versatility of the upper stage, increase its scalability, thereby reducing development costs and time, and reducing technical risks. It can also be used for different missions such as low Earth orbit, high Earth orbit, and even deep space. It can also be combined with satellites to be carried by domestic and foreign rockets, establishing a convenient bridge between rockets and satellites. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0019] Figure 1 This is a front view of a scalable, general-purpose liquid upper stage spacecraft provided in the embodiments of this application;

[0020] Figure 2 This is a bottom view of a scalable, general-purpose liquid upper stage spacecraft provided in the embodiments of this application. Detailed Implementation

[0021] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. Additionally, spatial relationship terms such as "upper," "lower," "left," "right," "front," and "rear" are used for ease of description to explain the positional relationship between two components. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application.

[0022] like Figure 1 and Figure 2As shown, this application provides a scalable and universal liquid upper stage spacecraft, including: an upper stage body 110, an extension section 120, an instrument mounting platform 130 and a support (not shown in the figure), as well as an interconnected flight control system, avionics system and propulsion system; the avionics system and flight control system are existing systems, and the interconnection between the avionics system, flight control system and propulsion system is also existing. The avionics system ensures precise control and information exchange during flight, the flight control system ensures flight along a predetermined trajectory by controlling the thrust and direction of the propulsion system, and the propulsion system adjusts the thrust according to the instructions of the flight control system to achieve precise control.

[0023] The upper stage body 110 has a docking interface at its upper edge for docking and fixing with the lower edge of the extension 120 of another liquid upper stage spacecraft used for expansion. The lower edge of the upper stage body 110 docks and is fixed with the upper edge of the extension 120. The lower edge of the extension 120 has a docking interface for docking and fixing with the rocket's final stage.

[0024] Optionally, the diameter of the upper stage body 110 and the extension section 120 is 3.2m, and the total height of the upper stage body 110 and the extension section 120 is 3.2m. Alternatively, the lower edge of the upper stage body 110 is connected to the upper edge of the extension section 120 by means of explosive bolts and a separation spring. During separation, the explosive spring ensures cold separation, and the extension section 120 and the rocket's final stage separate from the upper stage body 110 as a whole. Still alternatively, the inner side of the docking interface at the upper edge of the upper stage body 110 is lower than the outer side, and the inner side of the docking interface at the lower edge of the extension section 120 is higher than the outer side, so that the upper edge of the upper stage body 110 can dock with the lower edge of the extension section 120 used for extension.

[0025] The instrument mounting platform 130 is fixed inside the upper stage main body 110, and the instruments of the flight control system and avionics system are mounted on the instrument mounting platform 130. The avionics system consists of an onboard system and a telemetry, launch, and control system; the onboard system provides telemetry, external measurement, space-based telemetry and control, and image measurement functions; the telemetry, launch, and control system adopts a distributed integrated system, consisting of front-end and back-end equipment, which communicate with each other via a switch backbone network. The flight control system consists of a navigation, guidance, and attitude control system; the navigation system uses a ten-indicator redundant strapdown inertial measurement unit (SMU) combined with a GNSS receiver for integrated navigation; the guidance system uses an iterative guidance system; the attitude control system uses a ten-indicator redundant strapdown inertial measurement unit (SMU) + engine dual-swing + auxiliary power system.

[0026] The support is fixed inside the upper stage body 110 and located below the instrument mounting platform 130. The engine system 141 of the power system is detachably connected to the middle position of the support. The engine system 141 transmits thrust through the support to the upper stage body 110. All the tanks 142 of the power system are detachably and uniformly connected to the support, and a group of two tanks 142 are symmetrically distributed about the central axis of the support. The central axis of the support is coaxial with the central axis of the upper stage body 110 and the central axis of the extension 120. All the tanks 142 of the power system are connected to the engine system 141 to provide propellant to the power system 141.

[0027] Optionally, the engine system 141 of the propulsion system includes: one 20kN extrusion main engine, twelve 25N nozzles, and a dual-swing main engine. Attitude control and bottoming during the taxiing phase are achieved through the 25N nozzles. Alternatively, the propulsion system has four propellant tanks 142, arranged in two groups, symmetrically and uniformly detachably connected to the support frame. Still optional, the propulsion system also includes three gas cylinders connected to the propellant tanks 142, used to pressurize the tanks storing oxidizer and the tanks storing propellant. Optionally, after the propellant tanks 142 are filled with propellant, the mass of the expandable general-purpose liquid upper stage spacecraft is 5.1t, and the takeoff thrust is 20kN.

[0028] Two identical, scalable, universal liquid upper stage spacecraft are manufactured. The avionics and flight control systems mounted on the instrument mounting platform 130 in the expanded liquid upper stage spacecraft are removed, as are the engine system 141 of the propulsion system mounted on the support frame. Multiple propellant tanks 142 of the propulsion system mounted on the support frame are retained. All propellant tanks 142 within this liquid upper stage spacecraft belong to the propulsion system of the lower liquid upper stage spacecraft and are connected to the engine system 141 of the lower liquid upper stage spacecraft, providing propellant to the propulsion system 141. Thus, depending on the fairing length, the expanded new liquid upper stage spacecraft has an eight-tank upper stage.

[0029] Because the engine system 141 is detachably connected to the middle position of the support, different engine systems 141 can be replaced. For example, one 20kN extrusion main engine of engine system 141 can be expanded into two 20kN extrusion main engines, thereby converting the liquid upper stage spacecraft into a new liquid upper stage spacecraft. Furthermore, because all tanks 142 are uniformly and detachably connected to the support and are symmetrically distributed in pairs, groups of tanks 142 can be disassembled as needed. For example, four tanks 142 can be directly disassembled into a group of two tanks 142 to achieve low-load flight, thus also converting the liquid upper stage spacecraft into a new liquid upper stage spacecraft.

[0030] Furthermore, since the upper edge of the upper stage body 110 has a docking interface, the lower edge of the extension 120 has a docking interface, and the docking interface at the upper edge of the upper stage body 142 can dock with the docking interface at the lower edge of the extension 120 of another scalable general-purpose liquid upper stage spacecraft, a new liquid upper stage spacecraft can be created.

[0031] This application presents a scalable and versatile liquid upper stage spacecraft that improves the versatility and expands the scalability of the upper stage, thereby reducing development costs and time, and mitigating technological risks. It is also adaptable to a wide range of missions, capable of performing satellite insertion missions, covering satellites of varying sizes from 0.1t to 20t, and can accommodate multiple satellite launches simultaneously. Furthermore, this application features good structural adaptability, a clear interface with the rocket's final stage, a mature separation mechanism, a clear interface with the satellite, minimal separation impact, and adaptability to common separation methods. It can accommodate fairings of different sizes and is compatible with various rockets. Typical missions it can achieve include 500km altitude sun-synchronous orbit, geostationary transfer orbit, and lunar transfer orbit. In addition, the propulsion system of this application has good scalability, allowing for easy addition or removal of tanks and engines to adapt to different launch capacities. It can also serve as an orbital platform or a deep space exploration platform, providing support for scientific experiments.

[0032] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from the spirit or essential characteristics of this application. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this application. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0033] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A scalable and versatile liquid upper stage spacecraft, characterized in that, include: The upper stage main body, extension section, instrument mounting platform and bracket, as well as the interconnected flight control system, avionics system and power system; The upper stage body has a docking interface at its upper edge for docking and fixing with the lower edge of the extension of another liquid upper stage spacecraft used for expansion. The lower edge of the upper stage body docks and is fixed with the upper edge of the extension. The lower edge of the extension has a docking interface for docking and fixing with the rocket's final stage. The instrument mounting platform is fixed inside the upper stage body, and the instruments of the flight control system and the avionics system are mounted on the instrument mounting platform. The bracket is fixed inside the upper stage body and located below the instrument mounting platform. The engine system of the power system is detachably connected to the middle position of the bracket. All the storage tanks of the power system are detachably connected to the bracket evenly, and the two storage tanks in a group are symmetrically distributed about the central axis of the bracket. All the storage tanks of the power system are connected to the engine system.

2. The scalable, universal liquid upper stage spacecraft according to claim 1, characterized in that, The diameter of the upper stage body and extension is 3.2m, and the total height of the upper stage body and extension is 3.2m.

3. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, The lower edge of the upper stage body is connected to the upper edge of the extension section and fixedly connected by explosion bolts and release springs.

4. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, The inner side of the docking interface at the upper edge of the upper stage body is lower than the outer side, while the inner side of the docking interface at the lower edge of the extension section is higher than the outer side.

5. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, The power system's engine system includes: one 20kN extrusion main engine and twelve 25N nozzles.

6. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, The power system has four storage tanks, which are divided into two groups. The two groups of tanks are symmetrically and evenly detachably connected to the support.

7. The scalable, universal liquid upper stage spacecraft according to claim 6, characterized in that, The power system also has three gas cylinders connected to the storage tanks, which are used to pressurize the storage tanks for storing oxidizer and the storage tanks for storing propellant.

8. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, After the propellant tanks are filled, the scalable general-purpose liquid upper stage spacecraft has a mass of 5.1t and a takeoff thrust of 20kN.

9. The scalable, universal liquid upper stage spacecraft according to claim 1 or 2, characterized in that, The liquid upper stage spacecraft used for expansion retains multiple tanks for the propulsion system mounted on a support frame; Furthermore, all the tanks within the liquid upper stage spacecraft belong to the propulsion system of the liquid upper stage spacecraft located below, and are connected to the engine system of the liquid upper stage spacecraft located below.

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