Three-stage semi-solid-liquid mixing rocket and flight trajectory

Abstract

The invention discloses a three-stage semi-solid-liquid hybrid rocket, and belongs to the technical field of aerospace, and the solid-liquid hybrid rocket comprises a power system, a rocket body structure system and an avionics system; the rocket body structure system comprises a structure part section, a binding mechanism, a separating device and a propellant storage box; the separation device and the propellant storage tank are arranged in the structural part section; the structural section comprises a first core stage, a second core stage, a third core stage, a fairing and a plurality of boosting stages; wherein the first-stage core and the third-stage core adopt solid engines, and the second-stage core adopts a liquid engine with liquid oxygen and kerosene as propellants. The three-stage semi-solid-liquid mixing rocket is higher in transport capacity and lower in manufacturing cost.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a three-stage semi-solid-liquid hybrid rocket and a flight trajectory. Background Art

[0002] Traditional launch vehicles generally use pure solid or pure liquid rocket engines. With the continuous development of aerospace technology, the requirements for rocket carrying capacity are constantly increasing. At the same time, with the rise of commercial aerospace, the manufacturing cost of rockets is strictly limited.

[0004] At present, there is only one medium-sized solid-liquid hybrid launch vehicle in China, the Chang Liujia, but its manufacturing cost is high and cannot meet the requirements of commercial aerospace. How to combine mature solid and liquid modules to construct a new type of solid-liquid hybrid rocket with stronger carrying capacity and better cost-effectiveness to meet the needs of more satellite network launches is a key technical problem that needs to be solved urgently. Summary of the invention

[0005] In order to solve the above-mentioned technical problems, the present application provides a three-stage semi-solid-liquid hybrid rocket and a flight trajectory. The core first stage and core third stage of the three-stage semi-solid-liquid hybrid rocket use solid engines, and the core second stage uses a liquid engine. It has stronger carrying capacity and lower manufacturing cost than existing rockets with the same carrying capacity.

[0006] A three-stage semi-solid-liquid hybrid rocket, comprising: a rocket body structure system, a power system and an avionics system; The rocket body structure system includes a structural section, a binding mechanism, a separation device and a propellant tank; the separation device and the propellant tank are both arranged inside the structural section; The structural section includes a core stage, a core stage, a core stage, a fairing and a plurality of booster stages; the core stage, the core stage and the core stage are connected detachably in sequence; a payload is fixed inside the fairing; a plurality of booster stages are detachably connected to the side of the core stage; The power system includes a core first-stage engine, a core second-stage engine, a core third-stage engine and a booster engine; the core first-stage engine is a solid rocket engine, which is fixedly installed on the core first stage; the core second-stage engine is a liquid rocket engine with liquid oxygen and kerosene as propellants, which is fixedly installed on the core second stage; the core third-stage engine is a solid rocket engine, which is fixedly installed on the core third stage; the booster engine is a solid rocket engine, which is fixedly installed on the booster stage.

[0007] Preferably, the solid rocket engine adopts a flexible nozzle form controlled by an electromechanical servo mechanism; and the liquid engine adopts a bidirectional swinging nozzle form.

[0008] Preferably, the power system also includes a terminal attitude control power system for providing the rocket with pitch, yaw, and roll control capabilities and completing the rocket's terminal velocity correction work before the separation of the satellite and rocket; the terminal attitude control power system adopts a bipropellant and constant pressure extrusion liquid supply working mode.

[0009] Preferably, the total length of the three-stage semi-solid-liquid hybrid rocket is 33m; the take-off weight of the three-stage semi-solid-liquid hybrid rocket is 412t.

[0010] Preferably, the working time of the booster engine is 97s, and the takeoff thrust of a single booster stage in an atmospheric environment is 1534.5kN; the working time of the core first stage engine is 85s, and the takeoff thrust in a vacuum environment is 2324kN; the working time of the core second stage engine is 180s, and the takeoff thrust in a vacuum environment is 708.4kN; the working time of the core third stage engine is 52s, and the takeoff thrust in a vacuum environment is 180kN.

[0011] Preferably, the number of the booster stages is 4; and the total take-off thrust of the 4 booster engines is 6138 kN.

[0012] Preferably, the take-off weight of the booster stage flight phase is 412t; the take-off weight of the core stage flight phase is 136.5t; the take-off weight of the core stage two flight phase is 56.1t; and the take-off weight of the core stage three flight phase is 9.8t.

[0013] Preferably, the diameter of the booster stage is 2.65m; the diameter of the first core stage is 2.65m; the diameter of the second core stage is 3.35m; the diameter of the third core stage is 3.35m; and the diameter of the fairing is 4.2m.

[0014] According to another aspect of the present application, a three-stage semi-solid-liquid hybrid rocket launch process is also provided, and the launch process is performed on the three-stage semi-solid-liquid hybrid rocket, including: The sub-stage final assembly of the rocket is completed at the AIT Center: the engine / structural section approach and parking, the onboard equipment approach and storage, the weighing before final assembly, the equipment installation, the cable laying, the pyrotechnics installation, the engine servo system installation, the sub-stage assembly, the satellite cover assembly, and the full rocket stage joint test. After the test is completed, the attitude control power system is filled and inflated at the end, and the fairing valve cover, the adapter ring and the satellite bracket are docked with the satellite to form the satellite cover assembly. Transfer each sub-stage to the final assembly technical area: After each sub-stage is transferred to the final assembly technical area, it is erected in turn for vertical final assembly, and after completion, the rocket body is docked and tested and the cabin is cleaned and sealed; the satellite cover assembly is vertically transported to the launch area, and docked with the core stage booster assembly, and then the satellite-rocket joint test and cabin cleaning are carried out. After normal, the rocket and the launch pad are rolled over and transferred to the launch ship or loaded onto a transport vehicle as a whole; The three-stage semi-solid-liquid hybrid rocket that has been assembled and tested will be transported to the sea or land launch area: the three-stage semi-solid-liquid hybrid rocket will be transported to the required launch point by a launch ship or transport vehicle, and once in place, the core second stage liquid oxygen and kerosene will be added, and the launch process test will be carried out. If it is normal, the rocket can carry out the launch mission.

[0015] According to another aspect of the present application, a three-stage semi-solid-liquid hybrid rocket flight trajectory is also provided, which is the flight trajectory of the three-stage semi-solid-liquid hybrid rocket, comprising: During the booster stage flight phase, multiple boosters work together. After the rocket ignites and takes off, it performs a program turn and a gravity turn. During the thrust reduction phase of the booster engine, the core first stage engine ignites. After the booster engine is exhausted and shut down, the booster stage separates. After the core first stage engine is exhausted and shut down, the fairing is separated, the core first stage is separated, and the core second stage engine is ignited; After the core-stage two engine is actively shut down, the core-stage two is separated and the core-stage three is ignited; After the core three stage is exhausted and shut down, the final correction attitude control power system works to complete the final velocity correction and attitude adjustment of the rocket's final stage and separate the rocket from the satellite; After the satellite and rocket separated safely, the rocket's final stage began to leave orbit and passivate.

[0016] Compared with the prior art, this application has at least the following beneficial effects: 1. The three-stage semi-solid-liquid hybrid rocket of the present invention adopts solid engines in the first and third core stages and a liquid engine in the second core stage, which has stronger carrying capacity.

[0017] 2. The three-stage semi-solid-liquid hybrid rocket of the present invention can have a take-off weight of 410 t and a carrying capacity of no less than 5.0 t at 800 km 89.5° LEO.

[0018] 3. The three-stage semi-solid-liquid hybrid rocket of the present invention has lower manufacturing cost than existing rockets with equivalent capacity.

[0019] 4. The carrier rocket of the present invention can be launched both at sea and on land, and the launch response cycle is controlled to be within 48 hours at the shortest. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings: Figure 1 It is a schematic diagram of the overall system of the three-stage semi-solid-liquid hybrid rocket of the present invention; Figure 2 It is a schematic diagram of the structure of the rocket body structure system and the power system of the present invention.

[0021] The above drawings include the following reference numerals: 11. Booster engine; 12. Core first stage engine; 13. Core second stage engine; 14. Core third stage engine; 15. Liquid launch booster and delivery system; 16. Terminal repair attitude control power system; 21. Structural sections; 22. Binding mechanism; 23. Separation device; 24. Propellant tank; 31. Control system; 32. Measurement system; 33. Safety control system; 34. Measurement and launch control system; 41. Assembly support equipment; 42. Transportation equipment; 43. Launch service support equipment; 44. Launch platform; 100. Power system; 200. Rocket body structure system; 300. Avionics system; 400. Launch support system; 201. Fairing; 202. Adapter ring; 203. Core second and third stage separation ring; 204. Booster stage oblique nose cone; 205. Booster stage tail section; 206. Core first stage tail section; 207. Core first and second stage separation ring; 208. Core first stage transition section; 209. Core first stage interstage; 210. Satellite; 211. Main lashing; 212. Lashing connecting rod; 213. Core second stage interstage. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0023] like Figure 1-Figure 2As shown, a three-stage semi-solid-liquid hybrid rocket includes: a power system 100, a rocket body structure system 200 and an avionics system 300. The rocket body structure system 200 includes a structural section 21, a binding mechanism 22, a separation device 23 and a propellant tank 24. The separation device 23 and the propellant tank 24 are both arranged inside the structural section 21. The structural section 21 includes a core stage 1, a core stage 2, a core stage 3, a fairing 201 and a plurality of booster stages. The core stage 1, the core stage 2 and the core stage 3 are detachably connected in sequence. A payload is fixed inside the fairing. A plurality of booster stages are detachably connected on the side of the core stage 1.

[0024] The power system 100 includes a core first stage engine 12, a core second stage engine 13, a core third stage engine 14 and a booster engine 11. Among them, the core first stage engine 12 is a solid rocket engine, which is fixed to the core first stage. The core second stage engine 13 is a liquid rocket engine with liquid oxygen and kerosene as propellants, which is fixed to the core second stage. The core third stage engine 13 is a solid rocket engine, which is fixed to the core third stage. The booster engine 11 is a solid rocket engine, which is fixed to the booster stage.

[0025] Among them, the safety control of the rocket flight process is jointly achieved by the avionics system 300 and the self-destruct device in the power system 100.

[0026] Specifically, in this embodiment, there are four booster stages.

[0027] The power system consists of 6 solid engines and 1 liquid power system.

[0028] Preferably, the solid rocket engine adopts a flexible nozzle form controlled by an electromechanical servo mechanism; the liquid engine adopts a bidirectional swinging nozzle form.

[0029] In addition, the power system also includes a terminal attitude control power system 16 for providing the rocket with pitch, yaw, and roll control capabilities and completing the rocket terminal velocity correction work before the satellite-rocket separation. The terminal attitude control power system 16 adopts a bipropellant and constant pressure extrusion liquid supply working mode.

[0030] Preferably, the total length of the three-stage semi-solid-liquid hybrid rocket is 33m and the take-off weight is 412t.

[0031] Preferably, the working time of the booster engine 11 is 97s, and the takeoff thrust of a single booster stage in an atmospheric environment is 1534.5kN; the working time of the core first-stage engine 12 is 85s, and the takeoff thrust in a vacuum environment is 2324kN; the working time of the core second-stage engine 13 is 180s, and the takeoff thrust in a vacuum environment is 708.4kN; the working time of the core third-stage engine 14 is 52s, and the takeoff thrust in a vacuum environment is 180kN.

[0032] In this embodiment, the number of booster stages is 4; the total takeoff thrust of the 4 booster engines 11 is 6138 kN.

[0033] In addition, according to the carrying capacity requirements and the design requirements of the launch vehicle, the booster stages can be an even number other than 4, and the booster stages are symmetrically arranged in pairs on both sides of the rocket axis.

[0034] Preferably, the take-off weight of the booster stage flight phase is 410t; the take-off weight of the core stage flight phase is 135t; the take-off weight of the core stage two flight phase is 53.4t; and the take-off weight of the core stage three flight phase is 10t.

[0035] Preferably, the diameter of the booster stage is 2.65m, and the charge of the booster engine 11 is 61t; the diameter of the core stage is 2.65m, and the charge of the core stage engine 12 is 70t; the diameter of the core stage 2 is 3.35m, and the propellant stored in the propellant tank is liquid oxygen and kerosene, with a filling amount of about 40t; the diameter of the core stage 3 is 3.35m, and the charge of the core stage 3 engine 14 is 3.3t; the diameter of the fairing is 4.2m.

[0036] Table 1 Overall parameters of three-stage semi-solid-liquid hybrid rocket

[0037] The rocket body structure system 200 also includes an adapter ring 202 , a core second and third stage separation ring 203 , a core first stage tail section 206 , a core first and second stage separation ring 207 , a core first stage transition section 208 , a core first stage inter-stage section 209 and a core second stage inter-stage section 213 .

[0038] A satellite bracket is fixed inside the fairing 201, and the satellite 210, as a payload, is fixed inside the fairing 201 through the satellite bracket. An oxidant tank and a fuel tank for storing liquid oxygen and kerosene, respectively, are arranged inside the second stage of the core.

[0039] The core second stage interstage 213 is fixedly arranged between the core second stage and the core third stage, and is used for the fixed connection between the core second stage and the core third stage. The distal end of the connection between the core second stage interstage 213 and the core third stage has a core second and third stage separation ring 209, and the core second and third stage separation ring 209 is used to realize the detachable fixed connection between the core second stage and the core third stage.

[0040] The final attitude control power system 16 is arranged on the side of the core third stage to provide lateral thrust and cooperate with the core third stage engine 14 to achieve attitude control.

[0041] The core first stage interstage 209 is fixedly connected to the core first stage transition section 208, and is arranged between the core first stage and the core second stage, and is sleeved on the outside of the core second stage engine 13, and is used for the fixed connection between the core second stage and the core first stage. The distal end of the connection between the core first stage transition section 208 and the core first stage interstage 209 has a core first and second stage separation ring 207, and the core first and second stage separation ring 207 is used to realize the detachable fixed connection between the core first stage and the core second stage. The core first stage tail section 206 is sleeved on the tail of the core first stage engine 12.

[0042] In addition, the booster stage also includes a booster stage oblique nose cone 204 and a booster stage tail section 205; the booster stage oblique nose cone 204 is fixedly connected to the end of the booster engine 11, and the booster stage tail section 205 is fixedly connected to the tail of the booster engine 11. The booster stage is fixedly connected to the core stage through a binding mechanism, which includes a main binding 211 and a binding connecting rod 212.

[0043] In addition, the power system 100 also includes a terminal attitude control power system 16 for providing the rocket with pitch, yaw, and roll control capabilities and completing the terminal velocity correction of the rocket before the separation of the rocket and the satellite. The terminal attitude control power system 16 adopts a bipropellant and constant pressure extrusion liquid supply working mode, and is provided with liquid propellant by the liquid propellant booster delivery system 15. The liquid propellant booster delivery system 15 includes a fuel tank, an oxidizer tank, and corresponding delivery devices.

[0044] As another embodiment of the present invention, the three-stage semi-solid-liquid hybrid rocket further includes: a launch support system 400. The launch support system 400 is a universal solution design that takes into account both land launch and sea launch, and includes assembly support equipment 41, transportation equipment 42, launch service support equipment 43 and a launch platform 44.

[0045] The avionics system 300 includes a control system 31, a measurement system 32, a safety control system 33, and a test, launch and control system 34. Among them, the measurement system 32 includes a ground-based telemetry system, an external measurement system, and a safety control system 33. The avionics system 300 adopts a universal and integrated design scheme to achieve the integration of power supply and distribution on the rocket and the integration of the main functions of control and measurement. The rocket adopts a 1553B+RS422 hybrid bus system, and realizes distributed measurement and control through the upper and lower dual-core control architecture of the flight control combination and the core level combination, which reduces the complexity of the equipment, reduces the weight of the equipment and cables, and improves reliability. The test, launch and control system adopts a shelf-based and combined approach.

[0046] The three-stage semi-solid-liquid hybrid rocket of the present invention takes into account both sea launch and land launch, which can effectively reduce the restrictions on the launch site, improve the flexibility of use and the large-scale launch capability. Demonstration and design work has been carried out in accordance with the launch in the sea area near Haiyang Oriental Spaceport and Wenchang, which are currently allowed for civil and commercial space launches. When launching at sea, the launch response cycle can be compressed to a minimum of 48 hours through different usage modes, with a faster launch response cycle.

[0047] This three-stage semi-solid-liquid hybrid rocket can include: 7-day daily launch mode and 48h rapid response mode when in use.

[0048] 7-day daily launch mode: 4 booster stages, core 1, core 2, core 3, and fairing 201 are stored separately. After receiving the launch mission, the core 1, core 2, and core 3 are assembled into a core stage assembly, which is then transferred to the launch area for vertical docking and testing of the core stage assembly, four boosters, and the star cover assembly, and finally launched.

[0049] 48h rapid response mode: After the four booster stages and the first core stage are vertically docked, the bundled module is stored as a whole, the second and third core stages are stored as a whole, and the fairing 201 is stored separately; after receiving the launch mission, each module is transported to the launch station to complete the vertical docking and testing of the bundled module, the second and third core assembly, and the star cover assembly, and the launch is completed in 48 hours.

[0050] In addition, the three-stage semi-solid-liquid hybrid rocket of the present invention has a high carrying capacity while having a fast launch response cycle. Through simulation calculation analysis, the carrying capacity of the three-stage semi-solid-liquid hybrid rocket of the present invention at 800km 89.5°LEO is not less than 5.0t.

[0051] A three-stage semi-solid-liquid hybrid rocket launch process is provided, and the launch process is performed on the three-stage semi-solid-liquid hybrid rocket. When launching at sea, the rocket adopts a "three-vertical" test and launch scheme. After the rocket components are complete, the sub-stage assembly, sub-stage testing, final repair filling, and satellite cover docking are completed in the AIT center in sequence, and the vertical assembly and satellite-rocket docking are completed in the shore technical workshop. The rocket is vertically transferred to the launch ship, maneuvered with the launch ship to the designated sea area, and the launch is carried out after the propellant filling and testing are completed.

[0052] The launch process of the three-stage semi-solid-liquid hybrid rocket specifically includes: The sub-stage final assembly of the rocket is completed at the AIT Center: the engine / structural section approach and parking, the onboard equipment approach and storage, the weighing before final assembly, the equipment installation, the cable laying, the pyrotechnics installation, the engine servo system installation, the sub-stage assembly, the satellite cover assembly, and the full rocket stage joint test. After the test is completed, the attitude control power system is filled and inflated at the end, and the fairing valve cover, the adapter ring and the satellite bracket are docked with the satellite to form the satellite cover assembly. Transfer each sub-stage to the final assembly technical area: After each sub-stage is transferred to the final assembly technical area, it is erected in turn for vertical final assembly, and after completion, the rocket body is docked and tested and the cabin is cleaned and sealed; the satellite cover assembly is vertically transported to the launch area, and docked with the core stage booster assembly, and then the satellite-rocket joint test and cabin cleaning are carried out. After normal, the rocket and the launch pad are rolled over and transferred to the launch ship or loaded onto a transport vehicle as a whole; The three-stage semi-solid-liquid hybrid rocket that has been assembled and tested will be transported to the sea or land launch area: the three-stage semi-solid-liquid hybrid rocket will be transported to the required launch point by a launch ship or transport vehicle, and once in place, the core second stage liquid oxygen and kerosene will be added, and the launch process test will be carried out. If it is normal, the rocket can carry out the launch mission.

[0053] Among them, when the three-stage semi-solid-liquid hybrid rocket is transported to the sea launch area after final assembly and testing, the launch ship can maneuver to the designated sea area, complete the propellant filling and testing, and then carry out the launch.

[0054] Based on the overall scheme and mission characteristics of the rocket, the flight trajectory of the three-stage semi-solid-liquid hybrid rocket of the present invention can be divided into a booster stage flight section, a core stage flight section, a core stage two flight section, a core stage three flight section, a satellite-rocket separation section, and a deorbit passivation section, specifically: The four boosters work together in the booster stage flight phase. After the rocket ignites and takes off, it performs a program turn and a gravity turn. During the thrust reduction phase of the booster engine, the core first stage engine ignites. After the booster engine is exhausted and shut down, the booster stage separates. After the core first stage engine is exhausted and shut down, the fairing is separated, the core first stage is separated, and the core second stage engine is ignited; After the core-stage two engine is actively shut down, the core-stage two is separated and the core-stage three is ignited; After the core three stage is exhausted and shut down, the final correction attitude control power system works to complete the final velocity correction and attitude adjustment of the rocket's final stage and separate the rocket from the satellite; After the satellite and rocket separated safely, the rocket's final stage began to leave orbit and passivate.

[0055] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0056] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0057] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0058] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A three-stage semi-solid-liquid hybrid rocket, characterized in that: include: Rocket body structure system, power system and avionics system; The rocket body structure system includes a structural section, a binding mechanism, a separation device and a propellant tank; The separation device and the propellant tank are both arranged inside the structural section; The structural section includes a core stage, a core stage, a core stage, a fairing and a plurality of booster stages; the core stage, the core stage and the core stage are connected detachably in sequence; a payload is fixed inside the fairing; a plurality of booster stages are detachably connected to the side of the core stage; The power system includes a core first-stage engine, a core second-stage engine, a core third-stage engine and a booster engine; the core first-stage engine is a solid rocket engine, which is fixedly installed on the core first stage; the core second-stage engine is a liquid rocket engine with liquid oxygen and kerosene as propellants, which is fixedly installed on the core second stage; the core third-stage engine is a solid rocket engine, which is fixedly installed on the core third stage; the booster engine is a solid rocket engine, which is fixedly installed on the booster stage.

2. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The solid rocket engine adopts a flexible nozzle form controlled by an electromechanical servo mechanism; the liquid engine adopts a bidirectional swinging nozzle form.

3. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The power system also includes a terminal attitude control power system for providing the rocket with pitch, yaw, and roll control capabilities and completing the rocket's terminal velocity correction work before the separation of the satellite and the rocket; the terminal attitude control power system adopts a bipropellant and constant pressure extrusion liquid supply working mode.

4. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The total length of the three-stage semi-solid-liquid hybrid rocket is 33m; the take-off weight of the three-stage semi-solid-liquid hybrid rocket is 412t.

5. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The working time of the booster engine is 97s, and the takeoff thrust of a single booster stage in atmospheric environment is 1534.5kN; the working time of the core first stage engine is 85s, and the takeoff thrust in vacuum environment is 2324kN; the working time of the core second stage engine is 180s, and the takeoff thrust in vacuum environment is 708.4kN; the working time of the core third stage engine is 52s, and the takeoff thrust in vacuum environment is 180kN.

6. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The number of the booster stages is 4; the total take-off thrust of the 4 booster engines is 6138kN.

7. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The take-off weight of the booster stage flight phase is 412t; the take-off weight of the core stage flight phase is 136.5t; the take-off weight of the core stage two flight phase is 56.1t; and the take-off weight of the core stage three flight phase is 9.8t.

8. The three-stage semi-solid-liquid hybrid rocket according to claim 1, characterized in that: The diameter of the booster stage is 2.65m; the diameter of the first core stage is 2.65m; the diameter of the second core stage is 3.35m; the diameter of the third core stage is 3.35m; and the diameter of the fairing is 4.2m.

9. A three-stage semi-solid-liquid hybrid rocket launch process, characterized in that: The launching process of the three-stage semi-solid-liquid hybrid rocket according to any one of claims 1 to 8 comprises: The sub-stage final assembly of the rocket is completed at the AIT Center: the engine / structural section approach and parking, the onboard equipment approach and storage, the weighing before final assembly, the equipment installation, the cable laying, the pyrotechnics installation, the engine servo system installation, the sub-stage assembly, the satellite cover assembly, and the full rocket stage joint test. After the test is completed, the attitude control power system is filled and inflated at the end, and the fairing valve cover, the adapter ring and the satellite bracket are docked with the satellite to form the satellite cover assembly. Transfer each sub-stage to the final assembly technical area: After each sub-stage is transferred to the final assembly technical area, it is erected in turn for vertical final assembly, and after completion, the rocket body is docked and tested and the cabin is cleaned and sealed; the satellite cover assembly is vertically transported to the launch area, and docked with the core stage booster assembly, and then the satellite-rocket joint test and cabin cleaning are carried out. After normal, the rocket and the launch pad are rolled over and transferred to the launch ship or loaded onto a transport vehicle as a whole; The three-stage semi-solid-liquid hybrid rocket that has been assembled and tested will be transported to the sea or land launch area: the three-stage semi-solid-liquid hybrid rocket will be transported to the required launch point by a launch ship or transport vehicle, and once in place, the core second stage liquid oxygen and kerosene will be added, and the launch process test will be carried out. If it is normal, the rocket can carry out the launch mission.

10. A three-stage semi-solid-liquid hybrid rocket flight trajectory, characterized in that: The flight trajectory of the three-stage semi-solid-liquid hybrid rocket according to any one of claims 1 to 8 comprises: During the booster stage flight phase, multiple boosters work together. After the rocket ignites and takes off, it performs a program turn and a gravity turn. During the thrust reduction phase of the booster engine, the core first stage engine ignites. After the booster engine is exhausted and shut down, the booster stage separates. After the core first stage engine is exhausted and shut down, the fairing is separated, the core first stage is separated, and the core second stage engine is ignited; After the core-stage two engine is actively shut down, the core-stage two is separated and the core-stage three is ignited; After the core three stage is exhausted and shut down, the final correction attitude control power system works to complete the final velocity correction and attitude adjustment of the rocket's final stage and separate the rocket from the satellite; After the satellite and rocket separated safely, the rocket's final stage began to leave orbit and passivate.

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