A rocket zero-level boost launch well and method

Abstract

The application discloses a rocket zero-level boost launching well and a launching method, and belongs to the technical field of space launching. The launching well comprises an ultra-deep vertical well body, a bottom high-pressure steam power system, a well wall multi-stage sectional steam nozzle, a large-mass heat-insulation pressure-bearing piston, a manned spaceship and a top pressure relief and condensation recovery system. The outer wall of the piston is provided with elastic guide wheels and is slidably matched with the well wall track to realize central stable upward movement. The manned spaceship is detachably clamped on the upper end of the piston and does not directly contact with the well wall. When launching, the spaceship is not ignited in the well, and the piston and the spaceship are pushed upward by the bottom and well wall sectional steam static pressure, and the whole course overload is controlled within 1.5G-2.5G. After the spaceship is out of the well mouth, the engine is ignited to enter the orbit, the piston falls back, the steam is condensed and recovered, and the rapid reuse is realized. The application has the advantages of low overload, no ablation, high safety, extremely low cost, high-frequency repeated use and the like, and is suitable for low-cost manned space launching.

Description

Technical Field

[0001] This invention relates to a rocket zero-stage booster launch silo and launch method, belonging to the field of aerospace launch technology. Background Technology

[0002] Traditional rocket launches rely on high-temperature gas jets for takeoff, which has problems such as high overload, severe ablation, high cost, and difficulty in reuse, making it difficult to meet the needs of large-scale, low-cost, and highly safe manned spaceflight.

[0003] The United States has made electromagnetic launch technology its development goal for the next generation of space launch systems and has carried out a lot of research. However, although electromagnetic catapults can achieve zero-stage boost for rockets, they require an effective acceleration of far more than 10G to be economical and are not suitable for manned spacecraft boosting.

[0004] From a developmental perspective, the market needs a mild, safe, low-cost, and frequently reusable manned space launch system to address the pain points of existing launch methods, such as high overload, strong ablation, high cost, and difficulty in reuse. Summary of the Invention

[0005] In order to address the problems existing in the prior art, the present invention aims to provide a mild, safe, low-cost, and high-frequency reusable manned space launch system to solve the pain points of high overload, strong ablation, high cost, and difficulty in reuse of the existing launch methods.

[0006] To achieve the above objectives, the technical means adopted in this invention is as follows: a rocket zero-stage booster launch silo, comprising a manned spacecraft, a vertical silo body, a high-pressure aerodynamic system located at the bottom of the silo body, multi-stage air nozzles segmented on the silo wall, the air nozzles being connected to the high-pressure aerodynamic system, a pressure-bearing piston, the outer wall of the pressure-bearing piston being provided with elastic guide wheels, which slide and cooperate with guide rails set on the silo wall to achieve stable upward movement in a centered position; the bottom of the manned spacecraft is engaged with the upper end face of the pressure-bearing piston and does not directly contact the silo wall.

[0007] The manned spacecraft is directly attached to the upper end face of the piston, without contacting the well wall, resulting in no wear, no disturbance, and a simpler structure.

[0008] Furthermore, the high-pressure pneumatic power system adopts a high-pressure steam power system to provide high-pressure steam; the gas nozzles are distributed axially along the well wall and are set in a segmented multi-stage configuration, with multi-stage steam injection to achieve graded sequential boosting.

[0009] Furthermore, the steam is generated by heating one or more energy sources, including nuclear power, geothermal energy, solar energy, and thermal power.

[0010] Furthermore, the steam temperature is controlled at 300℃±5%, preventing high-temperature erosion and ensuring no structural damage to the well body, piston, or spacecraft.

[0011] Furthermore, a pressure relief and condensate recovery system is installed at the top of the vertical well body for steam recovery and recycling.

[0012] Furthermore, the vertical wellbore has a depth of 2000m to 3000m, providing space for long-stroke, gentle acceleration.

[0013] Furthermore, the pressure-bearing piston is made of heat-insulating material, and the outer wall is equipped with elastic guide wheels that slide in close contact with the well wall track to ensure centering, stability, and no swaying; the pressure-bearing piston undertakes the functions of guidance, friction, impact and sealing.

[0014] A launch method for a rocket zero-stage booster launch silo: During launch, the spacecraft does not ignite inside the vertical silo. The pressure-bearing piston is pushed by the multi-stage gas nozzles at the bottom and on the silo wall in stages, which drives the spacecraft upward along the silo. The overload is controlled between 1.5G and 2.5G throughout the process. After the spacecraft exits the silo, the engine ignites and enters orbit. At this time, the piston falls back, and the steam is condensed and recovered, achieving rapid reuse.

[0015] Compared with the prior art, the beneficial technical effects of the present invention are as follows: 1. Extremely low overload: Suitable for the elderly and children; 2. No ablation, no explosion: Compared to 3000℃ gas, 300℃ steam results in an extremely long equipment lifespan; 3. Extremely low cost: Energy cost is 1 / 100 of that of traditional rockets, and the overall launch cost can be reduced to 1 / 3 to 1 / 6 of that of traditional methods; 4. Quickly reusable: No major overhaul, no need to change fuel, and can be taken back to flight in 1 hour; 5. The project is feasible: the structure is simple and reliable, and fully conforms to the laws of classical physics; 6. By boosting the rocket's initial velocity to 300–800 m / s, 30–50% of the first-stage fuel can be saved, and the payload can be increased by 40–100% for the same takeoff mass; 7. High-frequency launch: The catapult system can be reset in 1-2 hours, supports daily launch frequency, and is compatible with constellation networking; This invention has the advantages of low overload, no ablation, high safety, extremely low cost, and high frequency reusability, making it suitable for low-cost manned space launches. Attached Figure Description

[0016] Figure 1 This is a diagram of the launch well and steam circulation system of the present invention; Figure 2 This is a schematic diagram of the pressure-bearing piston of the present invention; Figure 3 This is a schematic diagram of the cross-sectional structure of the pressure-bearing piston of the present invention; In the diagram: 1. Launch silo; 101. High-pressure boiler; 102. High-pressure pipeline; 103. High-pressure tank; 104. Electric valve; 105. Return water pump; 106. Depressurization condensate chamber; 2. Pressure-bearing piston; 201. Pressure-bearing piston seal; 202. Lubrication pipeline; 203. Nozzle; 204. Piston support; 205. Guide wheel; 3. Lubricant pump; 301. Lubrication pump piston; 302. Lubrication pump piston rod; 303. Lubricant piston chamber; 4. High-temperature resistant top plate; 401. Rocket support. Detailed Implementation Example

[0017] like Figure 1 , 2 The rocket zero-stage booster launch silo shown in Figure 3, Launch silo 1 has a depth of 2.8 km, is equipped with a guide rail, and has a pressure-bearing and sealing structure. It also has multiple steam nozzles installed in sections on the silo wall.

[0018] The bottom high-pressure steam power system includes a high-pressure boiler 101 and a high-pressure pipeline 102 connected to the high-pressure boiler 101. The high-pressure pipeline 102 is connected to a segmented multi-stage steam nozzle through a high-pressure tank 103 and an electric valve 104. The segmented multi-stage steam nozzle is distributed in multiple stages from bottom to top along the well body axis. The pressurization and timing control system controls the operation of steam and controls the timing-stage injection.

[0019] The large-mass heat-insulating and pressure-bearing piston 2 is made of composite materials and has the characteristics of heat insulation and pressure bearing. The sliding seal is set in the well body. The heat-insulating and pressure-bearing piston has the functions of sealing, pressure bearing and heat insulation.

[0020] A lubricant pump 3 is installed at the bottom center of the pressure piston 2. The lubricant pump 3 includes a lubricant pump piston 301 located in the lubricant piston chamber 303 of the pump body, and a lubricant pump piston rod 302 connected to the lubricant pump piston 301. The pump outlet is connected to a lubrication channel 202, and a nozzle 203 is installed at the end of the lubrication channel 202 for providing lubrication to the pressure piston.

[0021] Elastic guide wheels 205 are arranged circumferentially on the outer wall of the pressure-bearing piston 2. The elastic guide wheels 205 are mounted on the piston support 204 and slide in contact with the well wall guide rail to keep the piston centered and stable during upward movement, ensuring centering, stability, and no swaying. The pressure-bearing piston undertakes the functions of guidance, friction, impact, and sealing. The guide wheels 205 are hydraulically buffered and evenly distributed along the circumference of the piston to counteract lateral forces, reduce friction, and ensure smooth upward movement.

[0022] A high-temperature resistant top plate 4 is installed on the top of the pressure-bearing piston 2. A rocket support 401 is set on the high-temperature resistant top plate 4. The manned spacecraft is directly snapped onto the rocket support 401 on the upper part of the piston. The manned spacecraft is detachably snapped and fixed to the upper end face of the heat-insulated pressure-bearing piston 2, without direct contact with the well wall. The segmented steam nozzles adopt position-linked timing control, forming a steam thrust chamber only below the piston, which only pushes the piston and does not directly act on the spacecraft.

[0023] A depressurization and condensation recovery system is installed on the upper part of the launch well 1 for depressurization at the wellhead and condensation and circulation of steam working fluid. The system includes a depressurization condensation chamber 106 and a return water pump 105. The depressurization condensation chamber 106 is connected to the high-pressure boiler 101 through a return water pipe and the return water pump 105 installed on the return water pipe.

[0024] The entire launch process is as follows: steam staged booster → low overload exit from the silo → spacecraft ignition and orbit insertion → piston retraction → steam recovery.

[0025] The spacecraft is attached to the piston, and no ignition is performed inside the well. Steam is activated at the bottom, gently pushing the piston up. The nozzles on the well wall release steam in stages, pushing only the piston. The entire process is subjected to an overload of 1.5G to 2.5G, which is extremely safe. The spacecraft ignites and enters orbit the moment it exits the well. The piston falls back, the steam is condensed and recovered, and it can be launched again within half an hour.

[0026] Boosting the rocket's initial velocity to 300-800 m / s can save 30-50% of the first-stage fuel and increase the payload by 40-100% for the same takeoff mass. High-frequency launch: The ejection system can be reset in 1-2 hours, supporting daily launches and adapting to constellation networking. Cost reduction: The overall launch cost can be reduced to 1 / 3 to 1 / 6 of the traditional mode.

Claims

1. A rocket zero-stage booster launch silo, characterized in that: It includes a vertical well body, a high-pressure aerodynamic system located at the bottom of the well body, multi-stage air nozzles segmented on the well wall, the air nozzles connected to the high-pressure aerodynamic system, a pressure-bearing piston, and an elastic guide wheel on the outer wall of the pressure-bearing piston that slides in cooperation with the guide rail set on the well wall; the bottom of the manned spacecraft is engaged with the upper end face of the pressure-bearing piston and does not directly contact the well wall.

2. The rocket zero-stage booster launch silo according to claim 1, characterized in that: The high-pressure pneumatic power system adopts a high-pressure steam power system to provide high-pressure steam; the gas nozzles are distributed along the axial direction of the well wall vertically and are set in a segmented multi-stage configuration, with multi-stage steam injection to achieve graded sequential boosting.

3. The rocket zero-stage booster launch silo according to claim 2, characterized in that: The steam is generated by heating one or more energy sources, including nuclear power, geothermal energy, solar energy, and thermal power.

4. The rocket zero-stage booster launch silo according to claim 2, characterized in that: The steam temperature is controlled at 300℃±5%, with no high-temperature erosion, and no structural damage to the well body, piston, or spacecraft.

5. The rocket zero-stage booster launch silo according to claim 2, characterized in that: The top of the vertical well is equipped with a pressure relief and condensate recovery system for steam recovery and recycling.

6. The rocket zero-stage booster launch silo according to claim 1, characterized in that: The vertical wellbore has a depth of 2000m to 3000m, providing space for long-stroke, gentle acceleration.

7. The rocket zero-stage booster launch silo according to claim 1, characterized in that: The pressure-bearing piston is made of heat-insulating material, and the outer wall is equipped with elastic guide wheels that slide in close contact with the well wall track to ensure centering, stability and no sway. The pressure-bearing piston undertakes the functions of guidance, friction, impact and sealing. The top of the pressure-bearing piston is equipped with a rocket bracket and a high-temperature resistant top plate.

8. The launch method of the rocket zero-stage booster launch silo according to claim 1 is characterized in that: during launch, the spacecraft does not ignite in the vertical silo body, and the pressure-bearing piston is pushed by the multi-stage gas nozzles at the bottom and the silo wall in stages by static pressure, which drives the spacecraft to move upward along the silo body, with the overload controlled at 1.5G to 2.5G throughout the process; after the spacecraft exits the silo, the engine ignites and enters orbit; at this time, the piston falls back, the steam is condensed and recovered, and rapid reuse is achieved.

9. The rocket zero-stage booster launch silo according to claim 1, characterized in that... The pressure-bearing piston seal is provided with a lubricant pipeline and a nozzle in the middle. The nozzle is arranged in a circumferential array along the piston seal. The lubricant pipeline is connected to the lubricant pump in the middle of the pressure-bearing piston. The lubricant pump is powered by the high-pressure steam at the bottom of the pressure-bearing piston.

10. The launch method of the rocket zero-stage booster launch silo according to any one of claims 1 to 9, characterized in that, Includes the following steps: S1: The manned spacecraft is snapped and fixed to the upper end face of the heat-insulating and pressure-bearing piston, the well is sealed, and the spacecraft engine is not ignited. S2: Open the bottom main steam valve, and the high-pressure steam gently pushes the piston and the entire spaceship upward; S3: During the piston's upward movement, the segmented steam nozzles on the well wall open in stages according to their positions, continuously providing static pressure thrust; S4: By controlling the steam pressure and stroke, the overload is maintained between 1.5G and 2.5G throughout the launch process; S5: The spacecraft ignites its own engines the instant it reaches the wellhead and enters its predetermined orbit; S6: The piston falls back under the action of gravity, and the steam is condensed and recovered through the top system, and the system is quickly reset and reused.

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