Universal and modularized secondary configuration liquid carrier rocket

Abstract

The utility model provides a universal and modularized two-stage configuration liquid carrier rocket, which adopts a non-boosting configuration and comprises a first substage, a second substage, an upper stage and a fairing, the first sublevel is connected with the second sublevel; the second sublevel is connected with the upper sublevel; the fairing is connected with the upper stage, and the fairing is located at the foremost end of the carrier rocket; three first substage engines are arranged in the first substage; two second substage engines are arranged in the second substage; the distribution shape of the three one-substage engines is a linear layout for vertical recovery verification; in the returning process of the carrier rocket, the middle one-substage engine is started for the second time; and the upper stage adopts a standard upper stage. According to the invention, the gap of 2-2.5 ton capacity carrier rockets on the SSO orbit is filled up, and the carrier rocket is suitable for medium / small satellites, medium / low orbit networking launch and commercial carpooling launch.

Description

Technical Field

[0001] This application relates to the field of launch vehicle technology, and in particular to a universal, modular two-stage liquid launch vehicle. Background Technology

[0002] With booming demand in the commercial satellite sector, manufacturers of small and medium-sized satellites have sprung up like mushrooms after rain, and the launch of medium and low Earth orbit (LEO) constellations of these satellites accounts for a significant share of the satellite launch market. The domestic small satellite development field has transitioned from an "experimental application" stage to a "business service" stage, and the development of commercial satellites is gradually showing trends towards constellation-based, low-cost, mass production, and rapid manufacturing. While domestic launch demand is strong, constellation launches have not yet reached a large scale. How to cope with the explosive growth in demand for constellation launches is a major task for the future launch market.

[0003] A patent with publication number CN116335849A discloses a liquid-fueled launch vehicle for scientific experiments, which fills the gap in payload capacity between 1 and 2 tons, making it suitable for rapid launch missions, resupply launches, and commercial launches, especially for scientific payload launches. However, this launch vehicle cannot fill the gap in launch vehicles with a 2-2.5 ton capacity for SSO orbits.

[0004] Therefore, the urgent technical problem to be solved is how to provide a universal, modular two-stage liquid-fueled launch vehicle to fill the gap in launch vehicles with a capacity of 2-2.5 tons for SSO orbit. This launch vehicle is suitable for launching medium / small satellites, launching medium / low orbit satellite constellations, and commercial shared launches. Utility Model Content

[0005] The purpose of this application is to provide a universal, modular two-stage liquid-fueled launch vehicle to fill the gap in launch vehicles with a capacity of 2-2.5 tons for SSO orbit. This launch vehicle is suitable for medium / small satellite, medium / low orbit network launch, and commercial shared launch.

[0006] To achieve the above objectives, this application provides a universal, modular two-stage liquid-fueled launch vehicle. This launch vehicle adopts a booster-free configuration and includes: a first stage, a second stage, an upper stage, and a fairing; the first stage and the second stage are connected; the second stage and the upper stage are connected; the fairing is connected to the upper stage and is located at the foremost end of the launch vehicle; three first-stage engines are installed within the first stage; two second-stage engines are installed within the second stage; the three first-stage engines are arranged in a straight line for vertical recovery verification; one of the middle first-stage engines is restarted during the launch vehicle's return; the upper stage is a standard type.

[0007] The general-purpose, modular two-stage liquid-fueled launch vehicle described above includes an 85-ton-class liquid oxygen-kerosene engine for the first stage and a 30-ton-class vacuum version of the liquid oxygen-kerosene engine for the second stage.

[0008] The general-purpose, modular two-stage liquid-fueled launch vehicle described above has two second-stage engines distributed in two opposite quadrants of the four quadrants of the launch vehicle's cross-section.

[0009] The generalized, modular two-stage liquid-fueled launch vehicle described above, wherein both the first and second stages adopt general structural modules and are compatible with standard upper stages.

[0010] The general-purpose, modular two-stage liquid-fueled launch vehicle described above uses MON-3 and MMH as fuel for its second-stage engine.

[0011] The generalized, modular two-stage liquid-fueled launch vehicle described above, wherein the upper stage and the second stage are connected by an explosive bolt and a separation spring.

[0012] The general-purpose, modular two-stage liquid-fueled launch vehicle described above includes, within its second stage: a second-stage propellant tank.

[0013] The two-stage tank is adapted to the standard upper stage.

[0014] The general-purpose, modular two-stage liquid-fueled launch vehicle described above includes, within its first stage: a first-stage propellant tank.

[0015] The general-purpose, modular two-stage liquid-fueled launch vehicle described above, wherein the fairing adopts a standard fairing that is compatible with the standard upper stage.

[0016] The general-purpose, modular two-stage liquid-fueled launch vehicle described above, wherein the first stage and the second stage are separated and connected by explosive bolts and a forward and reverse thrust rocket method.

[0017] The beneficial effects achieved by this application are as follows:

[0018] (1) The launch vehicle of this application uses mature rocket standard modules and mature standard upper stage structure, shares the test and team in the development stage, reduces costs, and completes the development quickly.

[0019] (2) The launch vehicle first-stage engine design of this application can be used for vertical recovery flight test verification.

[0020] (3) The launch vehicle proposed in this application fills the gap in launch vehicles with a capacity of 2-2.5 tons in SSO orbit. This launch vehicle is suitable for medium / small satellites, medium / low orbit networking launches and commercial shared launches. Attached Figure Description

[0021] 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.

[0022] Figure 1 This is a structural schematic diagram of a generalized, modular two-stage liquid-fueled launch vehicle according to an embodiment of this application.

[0023] Figure 2 This is a schematic diagram of the layout of a first-stage engine according to an embodiment of this application.

[0024] Figure 3 This is a schematic diagram of the layout of a two-stage engine according to an embodiment of this application.

[0025] Reference numerals: 1-first stage; 2-second stage; 3-upper stage; 4-fairing; 11-first stage engine; 21-second stage engine. Detailed Implementation

[0026] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0027] like Figure 1 As shown, this application provides a universal, modular two-stage liquid-fueled launch vehicle. The launch vehicle adopts a booster-free configuration and includes: a first stage 1, a second stage 2, an upper stage 3, and a fairing 4; the first stage 1 and the second stage 2 are connected; the second stage 2 and the upper stage 3 are connected; the fairing 4 is connected to the upper stage 3 and is located at the foremost end of the launch vehicle; the first stage 1 is equipped with three first-stage engines 11; the second stage 2 is equipped with two second-stage engines 21; the three first-stage engines 11 are arranged in a "I"-shaped layout for vertical recovery verification; during the launch vehicle's return, the middle first-stage engine 11 can be restarted twice, meaning the middle first-stage engine 11 can be restarted in mid-air; the upper stage 3 is a standard type upper stage 3, which is a rocket upper stage 3 with certain universality, standardization, and typicality in design and function. Through capacity optimization, this type of launch vehicle has a payload capacity of 2.0-2.5 tons to a 500km / SSO orbit.

[0028] It's important to clarify that a boosterless rocket configuration refers to a rocket design that does not use additional boosters, relying solely on its own one or more stages to complete the launch mission. Compared to rockets with boosters, boosterless rockets have a simpler structure, primarily consisting of one or more stages within the rocket body itself, reducing the complexity of booster connections and separations. Boosterless rockets also exhibit a higher degree of integration, with greater cohesion between different parts of the rocket body and a more centralized internal system layout. This facilitates overall optimization during design and manufacturing, improving the rocket's overall performance and reliability.

[0029] As a preferred embodiment of this utility model, the launch vehicle of this application adopts a universal core stage with a diameter of 3.35m, a total length of about 40m, a takeoff mass of about 212t, and a takeoff thrust of about 255t.

[0030] As a specific embodiment of this utility model, the propulsion system of the launch vehicle includes a first-stage engine 11 and a second-stage engine 21. The first-stage engine 11 is an 85-ton-class liquid oxygen-kerosene engine; the second-stage engine 21 is a 30-ton-class vacuum version liquid oxygen-kerosene engine.

[0031] In a preferred embodiment of this invention, the three first-stage engines 11 have a total takeoff thrust of 255 tons and an engine specific impulse of 272s. Each second-stage engine 21 has a thrust of approximately 29 tons, and the total thrust of the two second-stage engines 21 is 58 tons, with an engine specific impulse of approximately 327s. The total thrust of the three first-stage engines 11 and the two second-stage engines 21 is 12kN, suitable for a standard upper stage. The first-stage engines 11 and 21 are the core components that generate the rocket's powerful thrust.

[0032] like Figure 2 The three first-stage sub-engines are arranged in the same straight line, and the three first-stage sub-engines have the same structure.

[0033] like Figure 3 As shown, the two second-stage engines 21 are distributed in two opposite quadrants of the four quadrants of the launch vehicle's cross-section, forming a "\" shape. The two second-stage engines 21 have identical structures.

[0034] In a preferred embodiment of this utility model, both the first stage 1 and the second stage 2 adopt universal structural modules and are compatible with standard upper stages. The first stage 1 uses the basic first stage module of the Liji-2 rocket. To maintain structural compactness and reduce structural mass, the second stage 2 preferably adopts a common-bottom propellant tank scheme with the first stage 1. The launch vehicle of this application adopts modular and combined development, utilizing the sub-stage modules of the rocket under development to adapt to standard upper stages.

[0035] In a preferred embodiment of this invention, the second-stage engine 21 uses MON-3 and MMH as fuel. MON-3 is a mixed oxide, mainly composed of nitrogen tetroxide (N2O4) and nitric oxide (NO). MMH is methylhydrazine, a liquid fuel with high energy density and good stability, commonly used in spacecraft propulsion systems.

[0036] In a preferred embodiment of this invention, the second stage 2 includes a second-stage tank adapted to a standard upper stage. In another preferred embodiment, the second-stage tank is approximately 5.5 meters long, and the standard upper stage is approximately 3 meters long. The first stage 1 includes a first-stage tank. Both the first-stage and second-stage tanks store large quantities of fuel and oxidizer to provide the engine with working substances; their structural design must meet the requirements of high strength, lightweight, and good sealing.

[0037] In a preferred embodiment of this utility model, the fairing 4 is a standard fairing, adapted to the standard upper stage 3. Preferably, the fairing 4 is a 3350M standard fairing or a 3350L standard fairing. The standard fairing is a general-purpose fairing with common specifications used for launch vehicles.

[0038] In a preferred embodiment of this invention, the upper stage 3 and the second stage 2 are connected by explosive bolts and a separation spring, and cold separation is achieved between the upper stage 3 and the second stage 2 using the same method. The first stage 1 and the second stage 2 are separated and connected by explosive bolts and a forward / reverse thrust rocket method. The payload and the upper stage 3 are cold separated by a strap unlocking mechanism and a separation spring.

[0039] It should be explained that the upper stage 3 and the second stage 2 are connected by explosive bolts and separation springs. During normal flight, the explosive bolts provide a stable connection between the upper stage 3 and the second stage 2, tightly binding them into a single structure and ensuring the structural stability and coordinated operation of each stage during flight. When separation is required, the explosive bolts are activated first, releasing the previously tight connection through an explosion. Then, the separation springs activate, using their stored elastic potential energy to quickly and smoothly push the upper stage 3 and the second stage 2 apart, achieving separation. Cold separation means that no high temperatures, flames, or other high-temperature effects are generated during this process, avoiding adverse effects on the rocket structure and subsequent flight, allowing for a relatively "gentle" interstage separation operation.

[0040] It should be explained that the first stage and the second stage are connected using explosive bolts and forward and reverse thrust rockets. The explosive bolts maintain the connection, while the forward and reverse thrust rockets are a crucial part of the subsequent separation mechanism, pre-positioned in the overall structure to prepare for the separation action. When separation is required, the explosive bolts detonate first, releasing the rigid connection. Immediately afterwards, the forward and reverse thrust rockets ignite. The forward thrust rocket provides thrust to propel the second stage to continue its flight, while the reverse thrust rocket generates reverse thrust to accelerate the first stage away from the second stage. Through this coordinated thrust action, the first stage and the second stage achieve a clean, efficient, and reliable separation, ensuring the stability of the rocket's subsequent flight attitude and the planned operation of all components.

[0041] It should be explained that the payload and upper stage 3 are connected via a strap release mechanism and a separation spring. When the strap is locked, it tightly secures the payload and upper stage 3, ensuring their relative stability during rocket flight. The separation spring, on the other hand, is in a state of energy storage, awaiting subsequent separation. When separation is required, the strap unlocks according to a predetermined command, releasing the constraint on the payload and upper stage 3. Then, the separation spring releases its elastic potential energy, gently separating the payload from the upper stage 3. This is also a cold separation, minimizing any potential impact or interference on the payload and allowing it to smoothly enter its intended orbit to carry out subsequent tasks.

[0042] It's important to explain that the rocket's basic stage (first stage 1 and second stage 2) is primarily responsible for providing powerful thrust in the initial stages of launch, enabling the rocket to overcome Earth's gravity as quickly as possible, leave the ground, and accelerate to a certain speed and altitude. The upper stage 3, after the basic stage has completed its initial acceleration mission, continues to deliver the payload into the designated orbit or perform more complex orbital maneuvers. The basic stage typically completes its mission within minutes to a dozen minutes after launch and then separates from the upper stage 3.

[0043] It should be explained that the launch vehicle adopts the "three-horizontal testing and launch mode" of horizontal assembly, horizontal testing, and horizontal transportation. After being transported to the launch site by motor vehicle and erected, the launch vehicle is removed, and the launch is carried out after testing and fueling.

[0044] The beneficial effects achieved by this application are as follows:

[0045] (1) The launch vehicle of this application uses mature rocket standard modules and mature standard upper stage structure, shares the test and team in the development stage, reduces costs, and completes the development quickly.

[0046] (2) The launch vehicle first-stage engine design of this application can be used for vertical recovery flight test verification.

[0047] (3) The launch vehicle proposed in this application fills the gap in launch vehicles with a capacity of 2-2.5 tons in SSO orbit. This launch vehicle is suitable for medium / small satellites, medium / low orbit networking launches and commercial shared launches.

[0048] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0049] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to implement and use the present invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the present invention can be implemented without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the present invention with unnecessary detail. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0050] The above description is merely an embodiment of this utility model and is not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this utility model should be included within the scope of the claims of this utility model.

Claims

1. A universal, modular two-stage liquid-fueled launch vehicle, characterized in that, The launch vehicle adopts a boosterless configuration and includes: a first stage, a second stage, an upper stage, and a fairing. The first stage and the second stage are connected; the second stage and the upper stage are connected; the fairing is connected to the upper stage, and the fairing is located at the foremost end of the launch vehicle; The first stage is equipped with three first-stage engines; the second stage is equipped with two second-stage engines. The three first-stage engines are arranged in a straight line for vertical recovery verification; the middle first-stage engine is restarted twice during the return of the launch vehicle. The upper level is a standard upper level.

2. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The first-stage engine is an 85-ton-class liquid oxygen-kerosene engine; the second-stage engine is a 30-ton-class vacuum version of the liquid oxygen-kerosene engine.

3. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The two second-stage engines are located in two opposite quadrants of the four quadrants of the launch vehicle's cross-section.

4. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, Both the first and second sub-levels adopt a general structural module and are compatible with standard upper-level modules.

5. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The second-stage engine uses MON-3 and MMH fuels.

6. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The upper stage and the second sub-stage are connected by an explosion bolt and a release spring.

7. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The second stage includes: a second-stage storage tank. The two-stage tank is adapted to the standard upper stage.

8. The universal, modular two-stage liquid-fueled launch vehicle according to claim 7, characterized in that, The sub-stage includes: a sub-stage storage tank.

9. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The fairing is a standard type fairing, which is compatible with the standard type upper stage.

10. The universal, modular two-stage liquid-fueled launch vehicle according to claim 1, characterized in that, The first stage and the second stage are separated and connected by explosive bolts and positive and negative thrust rockets.

Images