Low-cost high-efficiency recoverable rocket

Abstract

The application discloses a low-cost high-efficiency recyclable small-sized carrier rocket, belongs to the technical field of aerospace carrier, and aims to solve the technical difficulties of the existing recyclable rocket, such as redundant structure, high cost, low energy utilization rate, high attitude control difficulty and high operation threshold. The rocket adopts a double-layer stainless steel cylinder wall and a stainless steel spiral connection grid integrated structure, integrates three functions of structure bearing, high-pressure gas storage and heat insulation, and does not need to additionally set a storage tank and a heat insulation layer; adopts a 'two-end reverse thrust' attitude control layout, combines a high-altitude falling energy recovery system and an air power engine power generation system, realizes efficient energy utilization and 'power generation + power output' integration; adds unmanned plane type operation logic, supports seamless switching between automatic and manual modes, and reduces the operation threshold; adopts a modular design, adapts to high-frequency and low-cost launching requirements such as near-earth orbit small satellite launching and constellation network supplementing, can realize safe, accurate and repeatable recycling, greatly reduces launching and recycling costs, and has extremely high practical value and commercial promotion prospect.

Description

Technical Field

[0001] This invention belongs to the field of aerospace launch vehicle technology, specifically relating to a small launch vehicle that is reusable, energy-efficient, and easy to operate. It is suitable for scenarios such as low Earth orbit satellite launch, space experimental payload transportation, and suborbital flight, and is particularly well-suited for high-frequency, low-cost launch needs such as batch launches of small and medium-sized satellites and constellation replenishment. Background Technology

[0002] With the rapid development of the aerospace industry, the launch demand for small satellites in low Earth orbit and space experimental payloads is increasing, and commercial spaceflight has entered a stage of large-scale development. Traditional expendable launch vehicles have prominent problems such as high launch costs, low energy utilization, and serious resource waste. Moreover, the attitude control during recovery is difficult and the operation process is complex, requiring professional operators, which further increases the cost of use and the operational threshold, making it difficult to meet the demand for high-frequency, low-cost commercial launches.

[0003] Currently, the mainstream reusable rocket recovery technologies worldwide are mainly divided into three categories: First, vertical takeoff and landing (VTOL) technology, represented by the American Falcon 9, uses a bottom-mounted single-end engine for reverse thrust deceleration and grid fin aerodynamic attitude control. Its rocket body has a single-layer structure with separate designs for the storage tank, load-bearing capacity, and heat insulation. It has numerous parts, a bulky structure, relies on multiple main engines for repeated ignition, suffers from high wear and tear, has a limited reuse life, and requires a dedicated launch site and a sea-based recovery vessel, resulting in extremely high supporting costs. Second, suborbital vertical landing (SVR) technology, represented by Blue Origin's NewShepard and China's Zhuque-3, is essentially a replication of mature technologies without core structural innovation, resulting in high costs. Third, winged gliding recovery technology, which greatly increases the weight of the wing structure, leads to significant payload loss, has complex aerodynamic design, is expensive, difficult to maintain, is prone to stall at low speeds and low altitudes, and has poor safety.

[0004] In addition, existing reusable rockets have low energy utilization efficiency and fail to fully recover the kinetic and potential energy during the rocket's high-altitude descent. Attitude control relies mainly on single-end thrust reversers and grid fins, which are not effective for vertical attitude control of slender rocket bodies and are prone to tilting, oscillation, and other problems, affecting recovery safety. At the same time, existing reusable rocket control systems are complex, requiring operators to have professional rocket operation experience, which makes it difficult to learn quickly and limits their widespread application.

[0005] Therefore, developing a reusable rocket that is simple in structure, low in cost, energy efficient, has precise attitude control, and is easy to operate, in order to solve the pain points of existing technologies such as structural redundancy, high cost, energy waste, and complex operation, has become an urgent technical problem to be solved in the current aerospace field. Summary of the Invention

[0006] Purpose of the Invention: The purpose of this invention is to overcome the shortcomings of existing technologies and provide a low-cost, high-efficiency, reusable rocket. Through structural integration innovation, attitude control innovation, energy utilization innovation, and control mode innovation, it achieves an integrated design of "structural support + high-pressure gas storage + heat insulation," solving the problem of vertical attitude control for slender rocket bodies, improving energy utilization efficiency, simplifying control procedures, reducing launch and recovery costs, and achieving safe, accurate, and reusable rockets. This meets the actual needs of small-scale near-Earth orbit launch missions, breaks through existing reusable rocket technology barriers, and lowers the threshold for commercial spaceflight.

[0007] To achieve the above-mentioned objectives, the present invention adopts the following technical solution: a low-cost, high-efficiency, reusable rocket, comprising a main rocket body structure, a thrust reverser system, a cryogenic high-pressure gas storage system, an aerodynamic engine power generation system, a turbine motor power generation system, an high-altitude descent energy recovery system, a landing buffer system, a navigation and positioning system, and a central control system. Each system adopts a modular design and works collaboratively to achieve rocket launch, mission execution, and reusability.

[0008] Rocket body main structure: The main body of the rocket adopts a double-layer stainless steel integrated cylinder wall structure, which integrates three major functions: structural support, high-pressure gas storage, and heat insulation. Specifically, it includes an outer stainless steel plate, an inner stainless steel plate, and a stainless steel spiral connecting grid plate.

[0009] The outer stainless steel plate is made of corrosion-resistant and high-temperature resistant stainless steel, and the surface is treated with anti-corrosion and high-temperature resistance to withstand the impact of external airflow, protect the inner structure, reduce material costs while ensuring structural reliability.

[0010] The inner stainless steel plate is made of high-strength, high-pressure resistant stainless steel and serves as the inner wall of the high-pressure gas storage chamber. It can withstand the preset high-pressure gas pressure and ensure that there is no gas leakage.

[0011] The stainless steel spiral connecting grid uses the same material as the inner stainless steel plate and is firmly connected to the inner and outer stainless steel plates through a fully automated welding process. The weld joints need to be inspected for flaws to ensure the connection strength. A closed, high-pressure-resistant interlayer storage cavity is formed between the inner and outer stainless steel plates and the spiral connecting grid. The inner wall of the cavity is polished and sealed, eliminating the need for an additional heat insulation layer. The spiral flow channel formed by the spiral grid and the interlayer air layer naturally achieve heat insulation, which can effectively reduce the heat exchange between the low-temperature gas in the cavity and the outside.

[0012] The rocket has a gas output port at the tail and an auxiliary thrust reverser installation port at the nose. The middle section has an energy recovery device installation position and a navigation and positioning system installation compartment. The overall structure adopts a symmetrical design to ensure the stability of the rocket's center of gravity. The rocket can be reused a number of times to meet the preset usage requirements and is suitable for small launch missions to low Earth orbit.

[0013] Thrust Reverse System: It adopts a "two-pronged thrust reverse system" design, including a bottom main thrust reverse system and a head auxiliary righting thrust reverse system. The two work together to achieve attitude stability during the rocket's descent, hovering, and landing processes, and solve the problems of tilting and oscillation of the slender rocket body.

[0014] The bottom-mounted main thrust reverser system is installed at the bottom of the rocket and adopts a fully distributed array motor turbofan design. The turbofans are evenly distributed on the bottom end face of the rocket in a ring array. Each turbofan can be controlled independently and has redundancy backup function. The failure of a single turbofan will not affect the overall recovery. The turbofans use high-power-density turbine motors with stepless speed regulation function, which can precisely adjust the magnitude of the thrust reverser force to achieve rocket hovering, controlled descent, and correction of rocket horizontal deviation. The turbofans are equipped with stainless steel protective covers, which have waterproof, dustproof, and foreign object impact protection functions, improving the reliability of the system.

[0015] The head-assisted righting and thrust-reverse system is installed at a preset position in the rocket's head compartment. It uses small, high-response turbine motors, which are evenly distributed in the annular area of ​​the head compartment and arranged in two symmetrical groups. They can be started, stopped, and speed adjusted independently. The turbine motors have a fast response speed. When the navigation and positioning system detects that the rocket's attitude tilt exceeds a preset angle, it will automatically start the motor in the corresponding direction to generate reverse thrust, righting the rocket to a vertical state. It will continue to work before landing to ensure that the rocket lands vertically.

[0016] Low-temperature high-pressure gas storage system: This system is based on the double-layer stainless steel sandwich structure of the rocket body, eliminating the need for an additional independent storage tank, simplifying the structure and reducing costs. It is used to store a mixture of liquid oxygen and liquid nitrogen, which is compressed and stored in a low-temperature and high-pressure state.

[0017] The interlayer storage chamber is functionally divided into multiple independent areas, each equipped with an independent gas valve and pressure sensor, allowing for individual control of the gas supply and improving its flexibility and reliability. The inner wall of the chamber is coated with a low-temperature sealing layer, preventing gas leakage and reducing heat exchange. Each storage area is equipped with pressure and temperature sensors to monitor gas pressure and temperature in real time and transmit the data to the central control system. When the pressure exceeds a preset value, a pressure relief valve automatically opens to release some gas. When the temperature rises, a liquid nitrogen replenishment device is activated to maintain the gas's low-temperature state. The storage chamber is connected to an air-powered engine via high-pressure resistant stainless steel pipes, equipped with one-way valves and flow regulating valves for precise control of the gas delivery volume and to prevent gas backflow.

[0018] Aerodynamic engine power generation system: This system includes multiple small aerodynamic turbine engines, symmetrically installed at the bottom of the rocket's double-layer stainless steel sandwich layer, serving as backups for each other. They are installed in an embedded and fixed manner at the bottom of the sandwich layer structure, which neither occupies the external space of the rocket body nor damages the aerodynamic shape of the rocket body. The engine air intake is connected to the outside air through a reserved channel in the sandwich layer, and the exhaust port faces the tail of the rocket, and is arranged in coordination with the turbofan array of the bottom main retro-propulsion system.

[0019] The engine uses the low-temperature, high-pressure mixed gas stored at the bottom of the jacket as its core power source. Combined with the work done by the outside air, it realizes the complete working process of "gas expansion drive - turbine rotation - electrical energy conversion". Specifically, it is divided into the following four stages: gas source delivery and preheating: the low-temperature, high-pressure mixed gas is delivered to the engine intake end through a special high-pressure resistant stainless steel pipeline. The pipeline has a built-in preheating device that can quickly preheat the low-temperature gas to the preset temperature. The preheating process is controlled in real time by the central control system to ensure stable engine operation.

[0020] Gas expansion and turbine drive: The preheated high-pressure gas enters the engine combustion chamber and mixes thoroughly with the outside air. The mixture expands in a controlled manner in the combustion chamber, generating a high-speed airflow. The high-speed airflow impacts the turbine blades, driving the turbine to rotate at high speed, converting the pressure energy and thermal energy of the gas into the mechanical energy of the turbine rotation.

[0021] Energy conversion and power linkage: The turbine is rigidly connected to the coaxial turbine motor rotor. The high-speed rotation of the turbine directly drives the motor rotor to rotate. The motor converts mechanical energy into electrical energy through electromagnetic induction. After rectification and voltage stabilization, it outputs stable electrical energy to meet the power needs of various rocket systems. At the same time, the turbine motor transmits some mechanical energy to the bottom main retrorocket turbofan and the head auxiliary retrorocket motor through a high-strength gear transmission mechanism, realizing the integration of "power generation + power output" and reducing energy waste.

[0022] Exhaust gas utilization and emission: The gas after the work is completed is discharged through the engine exhaust port. When discharged, it generates a weak reverse thrust, which can help the bottom main reverse thrust system to counteract the impact force of the rocket falling. The discharged gas is mainly nitrogen and oxygen, with no toxic or harmful components, which meets environmental protection requirements. At the same time, a noise reduction device is set during the exhaust process to reduce the impact of exhaust noise on the rocket body structure.

[0023] Multiple engines work together to output electrical energy that meets the needs of various rocket systems. After the engines generate electricity, some of the energy is stored in high-energy lithium battery packs as backup power to cope with scenarios where engine power generation is insufficient or malfunctions.

[0024] The turbine motor power system: The turbine motor is coaxially connected to the aerodynamic engine and simultaneously connected to the bottom thrust reverser turbofan and the head auxiliary thrust reverser motor via a high-strength gear transmission mechanism, achieving "multi-purpose use." It serves as both a power generation component for the engine and a power component for the thrust reverser system, simplifying the system structure. During normal rocket descent, the aerodynamic engine drives the turbine motor to generate electricity, while the turbine motor drives the thrust reverser turbofan to rotate and generate thrust. When the rocket's descent speed reaches a preset value, the turbine motor switches to "power generation mode," using the kinetic energy of the rocket's descent to drive the turbine rotation, improving power generation efficiency and achieving energy recovery. The gear transmission mechanism has high transmission efficiency and features wear resistance, high temperature resistance, and overload protection. The turbine motor's operating mode is automatically switched by the central control system and can be precisely adjusted according to the rocket's descent speed, attitude, and power demand.

[0025] High-altitude descent energy recovery system: This system, relying on a turbine motor power system and a lithium battery pack, is one of the core innovations of this invention in efficient energy utilization. When the rocket deviates from its orbit and begins its high-altitude descent, and the descent speed reaches a preset value, the system automatically activates the energy recovery function. During the rocket's descent, gravitational potential energy is converted into kinetic energy, accelerating the rocket. At this time, the turbine motor switches to "power generation mode," using the descent kinetic energy to drive the turbine to rotate and generate electricity. Simultaneously, it generates a weak braking force to slow down the descent speed, achieving simultaneous "deceleration + power generation." Part of the generated electricity is supplied to various systems in real time, and the other part is stored in the lithium battery pack. The energy recovery efficiency meets the preset requirements, effectively recovering the energy during the rocket's high-altitude descent and reducing energy waste.

[0026] When the rocket's descent speed exceeds the preset safety value, the system automatically shuts down the energy recovery function and activates the bottom main thrust reverser system to increase the reverse thrust and ensure safe recovery; the lithium battery pack is equipped with an overcharge protection device to prevent overcharging from damaging the battery and extend its service life.

[0027] Landing Buffer System: This system is installed at the bottom of the rocket and has multiple sets of buffer devices evenly distributed around the retrorockets and turbofan array. It adopts a dual buffer structure of "hydraulic buffer + elastic buffer" to solve the problems of large impact and high site requirements of existing landing buffers.

[0028] The hydraulic buffer device uses a high-strength hydraulic cylinder, which can effectively absorb the impact force during landing; the cylinder is filled with low-temperature resistant hydraulic oil, which can adapt to the ambient temperature during rocket landing and has good shock absorption function.

[0029] The elastic buffer device uses a high-strength buffer pad installed at the bottom of the hydraulic buffer device. It can absorb the remaining impact force during landing and increase the friction with the ground to prevent the rocket from sliding after landing.

[0030] When the rocket descends to a preset altitude above the ground, the bottom main thrust system reduces the descent speed to a preset safe value. At the moment of landing, the buffer system is activated, the hydraulic cylinders retract, and the buffer pad contacts the ground. Both absorb the impact force together, and the buffer device automatically resets after landing. The bottom of the buffer device is equipped with anti-slip textures, which can adapt to various landing environments. It does not require a dedicated launch pad or a sea recovery vessel, thus reducing recovery support costs.

[0031] Navigation and Positioning System: This system is installed in the navigation cabin in the middle of the rocket. It adopts a dual-mode positioning method of "BeiDou navigation + GPS navigation". It can acquire the rocket's latitude, longitude and altitude data in real time and transmit the data to the central control system. The system is equipped with an inertial navigation module, which can work independently when the satellite signal is interrupted. The endurance meets the preset requirements and improves the reliability of positioning.

[0032] The system is equipped with gyroscopes and accelerometers, which can monitor the rocket's tilt angle, angular velocity, and acceleration in real time. When the rocket's attitude tilt exceeds the preset angle, it immediately sends a signal to the central control system to activate the head-assisted thrust reverser system and achieve rapid attitude correction.

[0033] The system uses a high-speed wireless transmission module, enabling real-time data transmission and command reception with the ground control center; multiple landing points can be preset, and the system automatically plans the optimal landing path to avoid obstacles, and can automatically adjust when the landing point is abnormal; the system is equipped with two independent hardware devices, which serve as backups for each other to ensure stable operation.

[0034] Central Control System: This system adopts an industrial-grade PLC controller, equipped with a data acquisition module, command output module, wireless communication module, and emergency backup module. It is installed in the control cabin in the middle of the rocket and has the ability to resist high temperature, vibration, and electromagnetic interference, adapting to the complex environment of rocket flight and recovery.

[0035] The core of this system features a newly added drone-style control logic, supporting seamless switching between "automatic mode" and "manual mode." The control process aligns with drone operating habits, which is the core innovation of this invention in simplifying operation and lowering the barrier to entry. In automatic mode, the system automatically completes the entire process of high-altitude descent, energy recovery, attitude adjustment, hovering, and landing based on preset programs and real-time data, without human intervention. In manual mode, operators can precisely adjust the rocket's descent speed, hovering altitude, and horizontal position using a drone-style remote controller. Command responses are timely, and control is smooth and lag-free. It also supports manual control from the ground, allowing manual switching when automatic control malfunctions, thus improving recovery safety.

[0036] The system features self-diagnostic capabilities, quickly identifying fault points in each system and automatically activating backup systems. When a fault cannot be resolved automatically, the system issues an emergency alarm, and the remote controller simultaneously vibrates to alert the operator. The operator can then switch to manual mode for an emergency landing. The system also includes a one-click reset function to restart non-core faulty systems. Furthermore, it stores all operational data during the recovery process, allowing for data export for post-operation analysis and optimization of system parameters. It also stores operation logs for easy review of the operation process. The system optimizes the collaborative logic of each system, aligning with the needs of drone operation and reducing the difficulty of operation; operators with basic drone operation skills can easily learn to use it. Attached Figure Description

[0037] Figure 1 This is a schematic diagram of the rocket as described in an embodiment of the present invention.

[0038] Figure 2 This is a bottom view of the rocket according to an embodiment of the present invention.

[0039] Figure 3 This is a cross-sectional view of the rocket double-layer helical grid plate according to an embodiment of the present invention.

[0040] Figure 4 This is a partial cross-sectional view of the bottom of the rocket according to an embodiment of the present invention.

[0041] Detailed description of the attached diagram: 1. Main body of the rocket; 2. Fairing; 3. Aerodynamic generator; 4. Air inlet for rocket descent power generation; 5. Launch thruster nozzle; 6. Landing support; 7. Electromagnetic control valve; 8. Ducted motor blades; 9. Double-layer stainless steel cylinder wall; 10. Stainless steel spiral grid; 11. Battery pack.

[0042] Figure 1 The rocket's overall shape and key component layout were showcased, including the top fairing, main body, aerodynamic generator, bottom drop-powered air intake, and launch thruster nozzle. The overall design features a symmetrical aerodynamic shape to ensure the rocket's center of gravity is stable.

[0043] Figure 2 The image shows the bottom of the rocket from below. The launch thruster nozzle is located in the center, and the outer ring array is arranged with ducted motor blades, bottom ducted generator motors, electromagnetic control valves, and landing supports. This enables reverse thrust deceleration, attitude control, and landing support functions. The distributed layout improves the reliability and fault tolerance of the recovery process.

[0044] Figure 3 The diagram shows a cross-section of the double-layered cylindrical wall of the rocket body. The double-layered stainless steel cylindrical wall and the intermediate stainless steel spiral grid plate form an integrated sandwich structure, which has multiple functions such as structural load-bearing, low-temperature and high-pressure gas storage and heat insulation. It eliminates the need for additional storage tanks and heat insulation layers, thus simplifying the structural design.

[0045] Figure 4 This is a partial cross-sectional view of the rocket's bottom, clearly showing the internal assembly relationship of the double-layer stainless steel cylinder wall, stainless steel spiral grid plate, energy storage battery pack, aerodynamic generator, bottom air inlet, ducted motor fan blades and main nozzle, realizing the integrated operation of airflow drive, power generation and storage and reverse thrust, reflecting the energy recovery and power linkage design of this invention.

[0046] The invention also includes a head-assisted righting and thrust reverser system, which is arranged inside the rocket's head and forms a two-end thrust reverser layout with the bottom thrust reverser system. This system works together to achieve rocket attitude righting and vertical landing control, solving the problem of attitude control for slender rockets.

[0047] Compared with existing technologies, this invention has the following significant advantages, highlighting the technological and commercial value of eight key innovations: Integrated structural innovation and substantial cost reduction: Adopting a double-layer stainless steel cylinder wall + spiral grid integrated composite structure, it achieves a three-in-one integration of "structural load-bearing + sandwiched gas storage chamber + thermal insulation protection," eliminating the need for separate storage tanks and insulation layers, reducing the number of parts, simplifying the structure, and lowering the rocket's weight and manufacturing difficulty; The use of low-cost, mature stainless steel materials to replace expensive aerospace alloys and carbon fiber significantly reduces material costs and simplifies the manufacturing process. Furthermore, the rocket is reusable, greatly reducing the cost per launch and recovery, effectively solving the problems of resource waste and high cost of traditional disposable rockets, as well as the structural redundancy and high cost of existing reusable rockets.

[0048] Innovative attitude control ensures high recovery safety: Adopting a "two-end reverse thrust" layout, the bottom main reverse thrust system provides the main reverse thrust, while the head auxiliary reverse thrust system quickly rights the rocket body. The upper and lower ends work together to balance the rocket, effectively solving the problem of vertical attitude control for a slender rocket body. Its resistance to crosswinds and airflow disturbances far exceeds that of the existing single-end reverse thrust + grid fin design. Combined with Beidou + GPS dual-mode navigation, the positioning is accurate and the attitude monitoring is reliable. Key systems are equipped with redundant backups, which can automatically switch to backup equipment in case of failure, further improving the reliability of recovery.

[0049] Innovative energy utilization, energy saving, environmental protection and high efficiency: The air-powered engine power generation system achieves integrated "power generation + power output", eliminating the need for an additional power source to drive the reverse thrust system; at the same time, the high-altitude descent energy recovery system uses the kinetic energy of the rocket during descent to drive the turbine to generate electricity, achieving "deceleration + power generation" simultaneously, effectively recovering the kinetic and potential energy of the rocket during descent and converting it into electrical energy for storage and utilization, reducing energy waste; using a mixture of liquid oxygen and liquid nitrogen, there are no toxic or harmful gas emissions, and the stainless steel rocket body is reusable, reducing environmental pollutants and meeting environmental protection requirements.

[0050] Innovative control mode significantly lowers the barrier to entry: The new drone-style control logic supports seamless switching between automatic and manual modes. The control process is tailored to drone operating habits, with timely command response and smooth operation. Operators do not need professional rocket control experience; only basic drone control knowledge is required to get started. This solves the problems of complex and highly professional control of existing reusable rockets, making it easier to promote and apply.

[0051] Innovative layout design significantly improves reliability: The bottom adopts a distributed layout of ring array ducted motors, with each group of turbofans being independently controllable and serving as backups for each other. The failure of a single unit does not affect the overall recovery, demonstrating strong fault tolerance. The electromagnetic control valves are grouped for precise attitude fine-tuning, further enhancing the stability and reliability of the recovery process.

[0052] Innovative landing buffering technology lowers the barrier to landing: The dual buffering structure of "hydraulic buffering + elastic buffering" can effectively absorb landing impact, adapt to simple land sites, eliminate the need for a dedicated launch pad and sea recovery vessel, significantly reduce recovery support costs, and improve the flexibility and applicability of rocket recovery.

[0053] Power linkage innovation improves system efficiency: The turbine motor achieves "multi-purpose use", serving as both a power generation component and a power component for the reverse thrust system. Power linkage is achieved through a gear transmission mechanism, which simplifies the system structure and improves energy utilization efficiency and system synergy.

[0054] Low-cost innovation throughout the entire process, with significant commercial advantages: From material selection, structural design, energy utilization to control mode, the entire process is innovated around the goal of low cost and high reusability. Stainless steel materials and integrated structure reduce manufacturing costs, energy recovery reduces energy consumption costs, and simple operation reduces labor costs. It is suitable for high-frequency, low-cost launch needs such as batch launch of small and medium-sized satellites and constellation replenishment, and has extremely high practical value and market prospects.

[0055] The present invention will be further described in detail below with reference to specific embodiments. These embodiments are only used to explain the present invention and do not constitute a limitation on the scope of protection of the present invention.

[0056] This embodiment provides a low-cost, high-efficiency, reusable rocket with the following specific structure: The main body of the rocket adopts a double-layer stainless steel integrated cylindrical wall structure with a symmetrical overall design to ensure the stability of the rocket's center of gravity; the outer stainless steel plate is made of corrosion-resistant and high-temperature resistant stainless steel, and the surface is sprayed with a high-temperature resistant anti-corrosion coating; the inner stainless steel plate is made of high-strength and high-pressure resistant stainless steel; the stainless steel spiral connecting grid plate is connected to the inner and outer plates by a fully automated welding process, and flaw detection is performed after welding; the inner and outer plates and the spiral connecting grid plate form a closed sandwich storage cavity, and the inner wall of the cavity is polished and sprayed with a low-temperature sealing coating to achieve the three-in-one functions of structural load-bearing, gas storage, and heat insulation.

[0057] In the thrust reverser system, the bottom main thrust reverser system uses a ring array of turbofans, each of which can be controlled independently and has redundant backup function; the head auxiliary righting thrust reverser system uses small high-response turbine motors, which are symmetrically distributed and can be automatically activated to right the tilted rocket body, forming a "two-head thrust reverser" attitude control layout to ensure the rocket body lands vertically.

[0058] In the cryogenic high-pressure gas storage system, a mixture of liquid oxygen and liquid nitrogen is stored in a cryogenic and high-pressure state. The jacketed storage chamber is divided into multiple independent areas, each equipped with a pressure sensor, temperature sensor, and pressure relief valve to monitor the gas status in real time and automatically regulate it. The high-pressure pipeline is made of high-pressure resistant stainless steel and is equipped with one-way valves and flow regulating valves to precisely control the gas delivery volume.

[0059] In the aerodynamic engine power generation system, multiple small aerodynamic turbine engines are symmetrically installed at the bottom of the interlayer, serving as backups for each other. Working together, they can output electrical energy to meet the needs of various rocket systems. The high-energy lithium battery pack serves as a backup power source to cope with scenarios where the engine power generation is insufficient or malfunctions, thus achieving the integration of "power generation + power output".

[0060] The turbine motor power system adopts a high-strength gear transmission mechanism, which can automatically switch between power generation mode and power mode, with high transmission efficiency and overload protection function; the high-altitude fall energy recovery system can effectively recover the energy of the rocket during the high-altitude fall process. When the fall speed exceeds the preset safety value, the recovery function is automatically shut down and the bottom main thrust reverser system is activated to ensure safety.

[0061] The landing buffer system is equipped with multiple buffer devices and adopts a dual buffer structure of "hydraulic buffer + elastic buffer". The hydraulic cylinder can effectively absorb the landing impact force, the buffer pad can increase the friction with the ground, and the bottom is equipped with anti-slip texture. It can adapt to a variety of land landing environments and does not require a marine recovery platform.

[0062] The navigation and positioning system adopts BeiDou + GPS dual-mode positioning, which is accurate. It is equipped with an inertial navigation module and dual backup hardware to ensure stable operation of the system. The wireless transmission module can realize real-time data transmission and command reception with the ground control center and automatically plan the optimal landing path.

[0063] The central control system uses an industrial-grade PLC controller, which is resistant to high temperatures, vibration, and electromagnetic interference. The drone-style operation supports seamless switching between automatic and manual modes, is equipped with fault self-diagnosis and one-key reset functions, and can store operating data and operation logs for easy review and optimization. Operators with basic drone operation skills can get started quickly.

[0064] The manufacturing and testing process for the reusable rocket in this embodiment is as follows: Component manufacturing: manufacture the rocket body structure, thrust reverser system, engine, navigation equipment and other components according to the design requirements, complete individual component testing, ensure that the performance of all components meets the standards, and eliminate individual component failures.

[0065] Overall assembly: Modularly assemble the various components, fix the aerodynamic engine, connect the high-pressure pipeline, transmission mechanism, etc., complete the system integration test, optimize the drone-style control logic and the coordination parameters of each system, and ensure the reliable coordinated operation of each system.

[0066] Flight test: First, a low-altitude flight test is conducted to test basic functions and handling feel; then, a medium-to-high-altitude flight test is conducted to test high-altitude stability and energy recovery effect; finally, a full-process flight test is conducted to simulate actual mission scenarios, verify the feasibility of the plan, optimize the parameters of each system, and ensure that the rocket can be safely and accurately recovered.

[0067] Recovery and maintenance: After the test flight is completed, the rocket can be put into use again after simple maintenance, checking the condition of each component and replacing worn parts, thus achieving repeated recovery and reducing the cost of a single launch.

[0068] The reusable rocket in this embodiment has a simple structure, low cost, high energy efficiency, precise attitude control, and convenient operation. It can achieve safe, accurate, and reusable recovery, effectively reducing the cost of small launch vehicles in low Earth orbit, improving launch efficiency, breaking through the existing technological barriers of reusable rockets, and is suitable for commercialization and popularization, with broad application value.

Claims

1. A low-cost, high-efficiency, reusable rocket, characterized in that, The rocket body comprises a main structure, a thrust reverser system, a cryogenic high-pressure gas storage system, an aerodynamic engine power generation system, a turbine motor power generation system, a high-altitude descent energy recovery system, a landing buffer system, a navigation and positioning system, and a central control system. These systems are modularly arranged and work together to complete rocket launch, orbit insertion, and vertical reusable recovery. The main body is a double-layered stainless steel integrated cylindrical structure, integrating structural support, high-pressure gas storage, and thermal insulation. It includes an outer stainless steel plate, an inner stainless steel plate, and a stainless steel spiral connecting grid sandwiched between them. The inner and outer stainless steel plates and the stainless steel spiral connecting grid form a closed, high-pressure resistant storage chamber. The inner wall of the chamber is polished and sealed, eliminating the need for an additional independent thermal insulation layer and storage tank structure. The thrust reverser system adopts a two-pronged thruster structure, including a bottom main thruster system and a front thruster system. The auxiliary righting and thrust reverser system features a bottom-mounted main thrust reverser system with a ring-shaped distributed array ducted turbofan layout, and a head-mounted auxiliary righting and thrust reverser system equipped with a high-response small turbine attitude control nozzle. This coordinated upper and lower counterbalance ensures a stable vertical landing of the rocket. The aerodynamic engine power generation system is symmetrically embedded at the bottom of the rocket's interlayer, using cryogenic, high-pressure mixed gas stored in the interlayer as a power source. Combined with external air intake, it integrates mechanical energy generation and thrust reverser output. The central control system incorporates UAV-style control logic, supporting seamless switching between fully automatic programmed landing and manual control modes, adopting mature UAV control logic to lower the barrier to entry for professional users. The high-altitude descent energy recovery system relies on the linkage between the turbine motor and the onboard energy storage battery pack, utilizing the oncoming airflow during the rocket's high-altitude descent to drive the fan blades, simultaneously achieving aerodynamic deceleration and self-generated energy storage.

2. The low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The outer stainless steel plate is made of high-temperature and corrosion-resistant stainless steel sheet with a high-temperature and corrosion-resistant coating on the surface; the inner stainless steel plate is made of high-strength and high-pressure resistant stainless steel; the stainless steel spiral connecting grid plate is welded to the inner and outer cylinder walls by fully automatic robot and undergoes non-destructive testing, and the interlayer cavity is sealed and pressure-bearing.

3. The low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The ducted turbofans of the bottom main thrust reverser system are evenly distributed in a ring around the bottom of the rocket body. Each ducted turbofan has independent electronic speed control and independent reversing, and has the ability to redundancy and fault tolerance for single unit failure. A stainless steel protective cover is installed on the outside of the turbofan.

4. The low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The head-assisted righting and thrust-reverse system has multiple attitude control turbine nozzles symmetrically arranged around the head, which has a fast response speed and can correct the tilt angle of the rocket body in real time, suppressing the slender rocket body sway and crosswind deviation.

5. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The low-temperature high-pressure gas storage chamber is divided into multiple independent sealed zones. Each zone is independently equipped with a pressure sensor, a temperature sensor, and a pressure relief valve. The chamber is connected to the power system through a high-pressure resistant pipeline, which is equipped with a check valve and a flow regulating valve.

6. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The aerodynamic engine power generation system goes through four processes in sequence: air source preheating, high-pressure gas expansion to drive the turbine, mechanical energy to electrical energy conversion, and controlled exhaust gas emission. Part of the generated electricity is used immediately by the airborne equipment, and part is stored in the high-energy lithium battery pack for backup.

7. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The turbine motor and the aerodynamic engine are coaxially linked and connected to the bottom ducted turbofan and the head attitude control mechanism respectively through a gear transmission mechanism, which can automatically switch between power drive mode and inertial power generation mode.

8. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The high-altitude fall energy recovery system automatically activates when the rocket's fall reaches a set threshold, using the oncoming airflow to drive the fan blades to generate electricity and produce aerodynamic drag to slow it down; when the fall speed exceeds the safety threshold, the recovery mode automatically shuts down and the counter-propulsion force is increased to force deceleration.

9. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The landing cushioning system adopts a composite structure of hydraulic and elastic cushioning, with multiple sets of cushioning outriggers evenly distributed along the bottom circumference to absorb landing impact. It is suitable for landing on simple land sites and does not require a professional marine recovery platform.

10. A low-cost, high-efficiency, reusable rocket according to claim 1, characterized in that, The navigation and positioning system adopts a dual-mode inertial navigation system combining BeiDou and GPS, and is equipped with attitude gyroscopes and acceleration sensors for real-time monitoring. The central control system adopts an industrial-grade anti-vibration and anti-electromagnetic interference controller, which has the functions of fault self-diagnosis, data storage and one-key reset.

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