Solid-liquid hybrid launch vehicle and its launch method

Abstract

This invention provides a solid-liquid hybrid launch vehicle and its launch method. The solid-liquid hybrid launch vehicle includes a rocket body and multiple boosters. The rocket body includes a first stage located at the tail end and a fairing located at the nose end. The payload of the launch vehicle is disposed within the fairing. The boosters are mounted to the first stage via explosive bolts. The first stage employs a solid-liquid hybrid rocket engine, and the boosters employ solid rocket engines. Each booster is equipped with a separation rocket, which provides the propulsion to move the booster away from the first stage. The separation rocket is associated with at least one of the explosive bolts, allowing the launch system of the separation rocket to be triggered by unlocking the explosive bolts. This invention achieves a launch vehicle scheme that ensures the commercial value and economic benefits of the launch vehicle while also possessing rapid response capabilities.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a solid-liquid hybrid launch vehicle and its launch method. Background Technology

[0002] A launch vehicle is a space launch vehicle composed of multiple stages. Typically, launch vehicles deliver payloads such as artificial Earth satellites, manned spacecraft, space stations, and space probes into their designated orbits.

[0003] Launch vehicles are commonly classified according to the propellant they use, such as solid rockets and liquid rockets. For example, my country's Long March 3 launch vehicle is a three-stage liquid rocket; the Long March 1 launch vehicle is a hybrid three-stage rocket, with the first and second stages being liquid rockets and the third stage being a solid rocket; and the United States' Pegasus launch vehicle is a three-stage solid rocket.

[0004] Liquid rocket engines have a complex overall structure, and their propellants are difficult to store and often corrosive and toxic, making them inconvenient to use and less safe. Solid rocket engines, on the other hand, have a simple structure, easy-to-store propellants, mature technology, and high reliability. However, they have lower specific impulse, relatively shorter operating time, and are more difficult to adjust thrust and perform repeated shutdowns and restarts.

[0005] The current requirements for launching small spacecraft urgently necessitate launch vehicles with rapid response capabilities to gain a competitive edge and quickly target targets. Furthermore, while considering commercial value, low-cost economic efficiency must also be prioritized. How to ensure the commercial value and economic benefits of launch vehicles while maintaining rapid response capabilities is a key technical challenge that existing launch vehicles need to address. Summary of the Invention

[0006] This invention provides a solid-liquid hybrid launch vehicle and its launch method, which addresses the shortcomings of existing technologies in balancing the economic benefits and responsiveness of launch vehicles, and realizes a launch vehicle scheme that can ensure the commercial value and economic benefits of the launch vehicle while also having rapid response capabilities.

[0007] This invention provides a solid-liquid hybrid launch vehicle, comprising a rocket body and multiple boosters; the rocket body includes a first stage located at the tail end and a fairing located at the nose end, the payload of the launch vehicle is disposed within the fairing, and the boosters are mounted to the first stage via explosive bolts; the first stage employs a solid-liquid hybrid rocket engine, and the boosters employ solid rocket engines; each booster is equipped with a separation rocket, which provides the power to move the booster away from the first stage; the separation rocket is associated with at least one of the explosive bolts, so that the launch system of the separation rocket can be triggered by unlocking the explosive bolts.

[0008] According to the present invention, a solid-liquid hybrid launch vehicle is provided, wherein an upper stage is provided inside the fairing, the payload is installed on the upper stage, and two sub-stages are connected in series from the first sub-stage to the upper stage by explosive bolts; the second sub-stage employs a solid-liquid hybrid rocket engine, and the upper stage employs a solid rocket engine.

[0009] According to the present invention, a solid-liquid hybrid launch vehicle is provided, wherein the solid-liquid hybrid rocket engine includes an oxidizer tank, a solid fuel tank, and a nozzle; an electric pump delivery system is provided between the oxidizer tank and the solid fuel tank; when the electric pump delivery system is not activated, the liquid oxidizer and the solid fuel are stored separately in the oxidizer tank and the solid fuel tank, forming a physically isolated state; when the electric pump delivery system is activated, the liquid oxidizer in the oxidizer tank is pressurized and delivered to the solid fuel tank, and the pyrolysis gas of the solid fuel in the solid fuel tank is mixed with the liquid oxidizer and combusted to provide propulsion power through the nozzle.

[0010] According to the present invention, a solid-liquid hybrid launch vehicle is provided, wherein the liquid oxidizer includes one or more of nitric acid, liquid oxygen, nitrous oxide, and hydrogen peroxide; and the solid fuel includes one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate, and paraffin.

[0011] According to the present invention, a solid-liquid hybrid launch vehicle is provided, wherein the nozzle is equipped with a thrust vector control system, and the thrust vector control system controls the flight trajectory of the launch vehicle during flight by controlling the swing angle of the nozzle.

[0012] According to a solid-liquid hybrid launch vehicle provided by the present invention, the first stage, the second stage and the upper stage are provided with an attitude control system, the attitude control system including a plurality of attitude control engines capable of providing radial propulsion.

[0013] According to a solid-liquid hybrid launch vehicle provided by the present invention, the first stage is provided with twelve mounting positions for mounting the boosters, and the number of boosters on the launch vehicle is two, three, four, six or twelve.

[0014] According to a solid-liquid hybrid launch vehicle provided by the present invention, the tail end of the first stage and / or the tail end of the booster are provided with a protective cover made of heat-resistant material.

[0015] The present invention also provides a launch method for a solid-liquid hybrid launch vehicle, applicable to any of the solid-liquid hybrid launch vehicles described above. The method includes: after completing launch preparations, simultaneously activating the solid rocket motor of the booster and the solid-liquid hybrid rocket motor of the first stage; after a period of flight, shutting down the solid rocket motor of the booster and activating the explosive bolts between the booster and the first stage; by unlocking the explosive bolts, triggering the launch system of the separation rocket, which provides power to move the booster away from the first stage; the solid-liquid hybrid rocket motor of the first stage continues to operate to propel the rocket body to continue flight.

[0016] According to the present invention, a launch method for a solid-liquid hybrid launch vehicle is provided, wherein an upper stage is provided within the fairing, the payload is mounted on the upper stage, and two sub-stages are connected in series from the first stage to the upper stage via explosive bolts. The second stage employs a solid-liquid hybrid rocket engine, and the upper stage employs a solid rocket engine. The method includes: after the solid-liquid hybrid rocket engine of the first stage operates continuously for a period of time, the explosive bolts between the first and second sub-stages are activated, causing the first and second sub-stages to separate; 1 to 3 seconds after the separation, the solid-liquid hybrid rocket engine of the second stage ignites and controls the second stage to correct its trajectory; after entering a predetermined trajectory, the solid-liquid hybrid rocket engine of the second stage shuts down, and the explosive bolts between the second stage and the upper stage are activated, causing the upper stage to enter a gliding phase; after correcting the gliding trajectory of the upper stage, the solid rocket engine of the upper stage ignites to deliver the payload into a predetermined orbit with a three-axis stable attitude; after entering the predetermined orbit, the upper stage releases the payload.

[0017] The solid-liquid hybrid launch vehicle and its launch method provided by this invention utilize a first stage employing a solid-liquid hybrid rocket engine and boosters employing solid rocket engines, both operating simultaneously during the launch phase. The solid rocket engine boosters offer a faster response time, providing sufficient acceleration to the launch vehicle in a short period. The first-stage solid-liquid hybrid rocket engine combines the advantages of both traditional solid and liquid rocket engines, offering high safety and reduced maintenance costs. Furthermore, the separation rocket provides the propulsion to move the boosters away from the first stage, improving the separation success rate and reducing losses from launch failures. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the solid-liquid hybrid launch vehicle provided by the present invention;

[0020] Figure 2 This is a schematic diagram of the installation relationship between the first stage and the booster of the solid-liquid hybrid launch vehicle provided by the present invention.

[0021] Figure label:

[0022] 100: Rocket body; 101: Payload; 110: First stage; 111: Oxidizer tank; 112: Solid fuel tank; 113: Nozzle; 120: Fairing; 121: Upper stage; 130: Second stage; 131: Attitude control engine; 200: Booster; 210: Separation rocket; 211: Protective shield. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0024] Rocket engines are the most important components of launch vehicles. Currently, the most commonly used rocket engines can be divided into three categories: liquid rocket engines, solid rocket engines, and hybrid rocket engines. Liquid rocket engines, widely used in aerospace transportation, have high fuel energy density and specific impulse, are easy to control flow and adjust thrust, and can be restarted multiple times after shutdown. However, their overall structure is complex, the propellants are difficult to store and often corrosive and toxic, making them inconvenient to use and less safe. Solid rocket engines have a simple structure, easy-to-store propellants, mature technology, and high reliability. However, they have a lower specific impulse, relatively shorter operating time, and difficulty in adjusting thrust and implementing repeated shutdowns and restarts. Hybrid rocket engines combine the advantages of liquid rocket engines (high specific impulse, adjustable thrust, and multiple shutdowns and restarts) with the advantages of solid rocket engines (easy storage, simple structure, high reliability, and low maintenance costs). They also possess superior economic performance and have good application prospects.

[0025] This invention provides a solid-liquid hybrid launch vehicle that combines a solid rocket engine and a solid-liquid hybrid rocket engine, fully utilizing the advantages of both to achieve a launch vehicle scheme that ensures both commercial value and economic benefits while also providing rapid response capabilities.

[0026] The following is combined with Figure 1 A solid-liquid hybrid launch vehicle according to a preferred embodiment of the present invention is described.

[0027] like Figure 1 As shown, the rocket body 100 includes a first stage 110, a second stage 130, and an upper stage 121 connected in series from the tail to the nose. Both the first stage 110 and the second stage 130 employ hybrid rocket engines, each including an oxidizer tank 111, a solid fuel tank 112, and a nozzle 113 with a thrust vectoring control system. The upper stage 121 employs a solid rocket engine and carries a payload 101, with a fairing 120 surrounding it. Solid rocket engine boosters 200 are strapped around the first stage 110. The first stage 110, second stage 130, and fairing 120 are all connected via explosive bolts, as are the first stage 110 and boosters 200. The booster 200 is also equipped with a separation rocket 210, which, after the explosive bolts are engaged and unlocked, triggers the ignition system of the separation rocket 210. The power provided by the separation rocket 210 propels the booster 200 rapidly away from the first stage 110. The separation rocket 210 is preferably located at the tail end of the booster 200. The tail end of the first stage 110 and / or the tail end of the booster 200 is preferably equipped with a heat-resistant protective cover 211, which improves the temperature resistance to the rocket tail flame and prevents damage to the first stage 110 after the separation rocket 210 is activated.

[0028] After the solid-liquid hybrid launch vehicle of the preferred embodiment described above completes its launch preparations, it simultaneously activates the solid rocket motor of booster 200 and the solid-liquid hybrid rocket motor of first stage 110. This utilizes the rapid response capability of the solid rocket motor to enable the launch vehicle to achieve the required acceleration for takeoff more quickly. After a period of flight, the solid rocket motor of booster 200 shuts down, and the explosive bolts connecting booster 200 and first stage 110 are activated. Unlocking the bolts triggers the ignition system of separation rocket 210, igniting it to provide power and propel booster 200 away from first stage 110. Through separation rocket 210, the separation of booster 200 from first stage 110 is more thorough, reducing the risk of collision during separation, increasing the success rate of rocket launch, and thus reducing losses due to launch failure.

[0029] The first stage 110 and the second stage 130 are powered by a hybrid solid-liquid rocket engine, in which the liquid oxidizer and solid fuel are physically isolated before ignition, resulting in high safety and reduced maintenance costs. The upper stage 121 and the booster 200 are powered by solid rocket engines, which have high thrust and high mass-to-weight ratio. This effectively reduces the size of the launch vehicle while shortening the flight time and improving rapid response capability when transporting the same mass of payload.

[0030] To better understand the above technical solution, the solid-liquid hybrid launch vehicle and its launch method of the present invention will be described in detail below with reference to specific embodiments.

[0031] According to the present invention, a hybrid solid-liquid rocket includes a rocket body 100 and multiple boosters 200. The rocket body 100 includes a first stage 110 at the tail end and a fairing 120 at the nose end. The payload 101 of the launch vehicle is disposed within the fairing 120. The boosters 200 are mounted to the first stage 110 via explosive bolts. The first stage 110 employs a hybrid solid-liquid rocket engine, and the boosters 200 employ solid rocket engines. Each booster 200 is equipped with a separation rocket 210, which provides the power to move the boosters 200 away from the first stage 110. The separation rocket 210 is associated with at least one explosive bolt, allowing the activation system of the separation rocket 210 to be triggered by unlocking the explosive bolt. Preferably, each booster 200 is connected to the first stage 110 via multiple explosive bolts, which are simultaneously unlocked during separation. After the explosive bolts are released, the launch vehicle's onboard computer sends an ignition command to the separation rocket 210's ignition system in real time. The separation rocket 210's ignition system can be set to ignite immediately or delay 0 to 1 second after receiving the command to ensure that the explosive bolts between the booster 200 and the first stage 110 are fully released when the separation rocket 210 starts. The fairing 120, as a protective mechanism for the payload 101, preferably has a conical shape capable of breaking through the air.

[0032] By employing a hybrid solid-liquid rocket engine in the first stage 110 and a solid rocket engine in the booster 200, both operating simultaneously during the launch phase, the solid rocket engine booster 200 offers a faster response time, providing sufficient acceleration to the launch vehicle in a short period. The hybrid solid-liquid rocket engine in the first stage 110 combines the advantages of both traditional solid and liquid rocket engines, resulting in high safety and reduced maintenance costs. Furthermore, the separation rocket 210 provides the propulsion to move the booster 200 away from the first stage 110, improving the separation success rate and reducing losses from launch failures.

[0033] The separation rocket 210, associated with at least one explosive bolt, can be a high-pressure gas container instead of a combustion-type chemical rocket. The ignition system of the separation rocket 210 can be activated by detecting the state of the explosive bolt via sensor circuitry; alternatively, the onboard computer of the launch vehicle can monitor the state of the explosive bolt and send an activation command to the ignition system of the separation rocket 210 when the explosive bolt is unlocked. Upon receiving the activation command, the ignition system of the separation rocket 210 executes the ignition task immediately or with a delay, igniting the chemical fuel within the separation rocket 210 or releasing high-pressure gas, depending on the type of separation rocket 210, to generate a force that causes the booster 200 to move radially away from the launch vehicle.

[0034] The solid-liquid hybrid launch vehicle provided by the present invention can be configured as a single-stage launch vehicle, a two-stage launch vehicle, or a multi-stage launch vehicle as needed. Preferably, as follows... Figure 1 As shown, the fairing 120 contains an upper stage 121, on which the payload 101 is mounted. From the first stage 110 to the upper stage 121, a second stage 130 is connected in series by explosive bolts. The second stage 130 uses a hybrid rocket engine, while the upper stage 121 uses a solid rocket engine.

[0035] Preferably, the upper stage 121 is equipped with a payload separation mechanism and is connected to the rest of the launch vehicle via an instrument compartment. After the upper stage 121 enters the predetermined orbit, the payload can be released through the payload separation mechanism. The explosive bolts between the various mechanisms of the launch vehicle can be any one or more of the following types: slotted type, shear pin type, steel ball type explosive bolts, and non-contamination explosive bolts.

[0036] The solid-liquid hybrid launch vehicle's launch process includes at least the following stages: the takeoff phase, where the first stage 110 and booster 200 start simultaneously; the first separation, where booster 200 detaches from the launch vehicle, and the first stage 110 continues to output power; the second separation, where the first stage 110 detaches, and the solid-liquid hybrid rocket engine of the second stage 130 outputs power; and the third separation, where the second stage 130 detaches, and the solid rocket engine of the upper stage 121 accurately responds and starts, pushing the payload 101 to the predetermined orbit.

[0037] Based on the characteristics of hybrid rocket engines and solid rocket engines, the first stage 110 and second stage 130 of the launch vehicle possess advantages such as high specific impulse, adjustable thrust, multiple shutdown and restart capabilities, and the ease of storage, simple structure, high reliability, and low maintenance costs of solid rocket engines. The booster 200 and upper stage 121, on the other hand, have high thrust and a high mass-to-weight ratio, requiring a smaller scale and shorter flight time for transporting the same mass payload, thus exhibiting a high degree of rapid response capability. Specifically, the solid rocket engine of upper stage 121 has a high mass-to-weight ratio and high thrust, allowing for a smaller fairing 120 and shorter flight time during the orbital insertion phase while transporting the same mass payload 101, thereby improving rapid response capability.

[0038] According to the present invention, a solid-liquid hybrid launch vehicle includes an oxidizer tank 111, a solid fuel tank 112, and a nozzle 113. An electric pump delivery system is provided between the oxidizer tank 111 and the solid fuel tank 112. When the electric pump delivery system is not activated, the liquid oxidizer and solid fuel are stored separately in the oxidizer tank 111 and the solid fuel tank 112, forming a physically isolated state. When the electric pump delivery system is activated, the liquid oxidizer in the oxidizer tank is pressurized and delivered to the solid fuel tank 112. The pyrolysis gas of the solid fuel in the solid fuel tank 112 is mixed with the liquid oxidizer and combusted to provide propulsion power through the nozzle 113.

[0039] The electric pump delivery system offers advantages such as low cost, system simplicity, low tank pressure, lightweight structure, wide variable thrust range, and flexible operating modes. By controlling the delivery power of the liquid oxidizer through the electric pump delivery system, the combustion power of the hybrid rocket engine can be adjusted in real time, facilitating the adjustment of the launch vehicle's thrust. When the electric pump delivery system is shut down, the liquid oxidizer stored in the oxidizer tank 111 and the solid fuel tank 112 are physically isolated from the solid fuel, providing a high level of safety. Furthermore, the start and stop of the hybrid rocket engine can be controlled at any time by controlling the electric pump delivery system, enabling the launch vehicle to adapt to more complex flight environments.

[0040] According to the solid-liquid hybrid launch vehicle provided by the present invention, the liquid oxidizer may be liquid oxygen, liquid fluorine, liquid nitrous oxide, hydrogen peroxide, and nitric acid, preferably including one or more of nitric acid, liquid oxygen, nitrous oxide, and hydrogen peroxide. The solid fuel mainly includes polymeric compounds and metal hydrides, preferably including one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate, and paraffin.

[0041] According to the present invention, a solid-liquid hybrid launch vehicle is provided, wherein the nozzle 113 is equipped with a thrust vector control system, which controls the flight trajectory of the launch vehicle during flight by controlling the swing angle of the nozzle 113.

[0042] Nozzle 113 can be a flexible nozzle or a ball-and-socket nozzle. It is understood that in this invention, the nozzle 113 can be used not only in the hybrid solid-liquid rocket engines of the first stage 110 and the second stage 130, but also in the solid rocket engines of the booster 200 and the upper stage 121. At any stage of the launch vehicle's flight, the swing angle can be adjusted via the thrust vector control system control tube 113, thereby enabling flexible control of the launch vehicle's flight trajectory at any time.

[0043] Furthermore, the solid-liquid hybrid launch vehicle of the present invention can also control its flight attitude in other ways, such as by installing a secondary fluid injection system at the nozzle 113 of the rocket engine, allowing liquid or gaseous fluid to be injected into the engine jet through the nozzle diffuser section. The injected fluid generates an oblique shock wave in the supersonic nozzle airflow, causing an imbalance in pressure distribution, thereby deflecting the airflow.

[0044] According to the solid-liquid hybrid launch vehicle provided by the present invention, the first stage 110, the second stage 130 and the upper stage 121 may also be equipped with an attitude control system, which includes a plurality of attitude control engines 131 capable of providing radial power.

[0045] like Figure 1 As shown, the attitude control engine 131 can be installed in the interstage section between the first stage 110 and the second stage 130. When the attitude control engine 131 is activated, it provides power to adjust the flight attitude of the launch vehicle in the radial direction by ejecting airflow in the radial direction of the launch vehicle. In practical applications, multiple attitude control engines 131 are preferably provided. These multiple attitude control engines 131 can be installed on the first stage 110, the second stage 130, and the upper stage 121 of the launch vehicle, or on any interstage section between the first stage 110, the second stage 130, and the upper stage 121, depending on the launch requirements. Preferably, the first stage 110 and the second stage 130 are each provided with four attitude control engines 131, and the upper stage 121 is provided with at least six attitude control engines 131, to meet the attitude control requirements of the launch vehicle during liftoff and orbit insertion.

[0046] Specifically, the preferred embodiment of the control system may include a helium cylinder, a high-pressure valve, a filter, a pressure-reducing valve, a solenoid valve, and an attitude control thrust chamber to form the attitude control engine 131. The helium cylinder is connected to the filter via the high-pressure valve. A pressure-reducing valve is located at the other end of the filter. A solenoid valve is located at the end of the pressure-reducing valve furthest from the filter, and the attitude control thrust chamber is located at the end of the solenoid valve furthest from the pressure-reducing valve. High-pressure helium gas is released from the helium cylinder to form a jet stream that provides radial power.

[0047] According to the solid-liquid hybrid launch vehicle provided by the present invention, based on the launch vehicle described in any of the preceding embodiments, different numbers of boosters 200 can be used depending on the launch vehicle's payload target to provide rapid initial acceleration during the initial flight phase of the launch vehicle.

[0048] Preferred options Figure 2As shown, the first stage 110 has twelve pre-installed mounting positions for boosters 200. Personnel can add the appropriate number of boosters 200 to the first stage 110 during the launch vehicle preparation phase, according to actual launch requirements. The number of boosters 200 on the launch vehicle can be two, three, four, six, or twelve.

[0049] Furthermore, under more complex flight conditions, multiple boosters 200 can be activated in batches, thus providing propulsion during flight phases beyond the initial takeoff phase. Taking a four-boost configuration as an example, during the operating time of the hybrid rocket engine of the first stage 110, two of the four boosters 200, which are relatively distributed, can be activated simultaneously with the first stage 110. The other two boosters 200 are activated when the first two boosters 200 are about to cease operation, thereby extending the operating time of the boosters 200.

[0050] According to the solid-liquid hybrid launch vehicle provided by the present invention, a heat-resistant protective shield 211 is provided at the tail end of the first stage 110 and / or the tail end of the booster 200. On the one hand, the protective shield 211 can improve the tolerance of the tail end of the first stage 110 and / or the tail end of the booster 200 to the tail heat temperature of the launch vehicle. On the other hand, the separation rocket 210 of the booster 200 is preferably provided at the tail end of the booster 200. When the separation rocket 210 is activated, the protective shield 211 on the first stage 110 can isolate the high-temperature gas ejected by the separation rocket 210 and prevent it from damaging the first stage 210.

[0051] Based on the solid-liquid hybrid launch vehicle described above, this invention provides a launch method for a solid-liquid hybrid launch vehicle, the method comprising: after completing launch preparation work, simultaneously starting the solid rocket motor of booster 200 and the solid-liquid hybrid rocket motor of first stage 110; after flying for a period of time, shutting down the solid rocket motor of booster 200 and activating the explosive bolt between booster 200 and first stage 110; by unlocking the explosive bolt, triggering the start-up system of separation rocket 210, separation rocket 210 provides power to move booster 200 away from first stage 110; the solid-liquid hybrid rocket motor of first stage 110 continues to operate to propel the rocket body 100 to continue flight.

[0052] The solid rocket motor of booster 200 can respond quickly during the start-up phase, providing a large amount of booster power to the launch vehicle in a short time. Combined with the power output of the hybrid solid-liquid rocket motor of first stage 110, this allows the launch vehicle to achieve sufficient takeoff acceleration in a short period. During booster 200 separation, the release of the explosive bolts triggers the separation rocket 210, providing the power to reliably separate booster 200 from first stage 110. This prevents accidental collisions during separation and improves the success rate.

[0053] The fairing 120 of the solid-liquid hybrid launch vehicle is equipped with an upper stage 121, and the payload 101 is installed in the upper stage 121. From the first stage 110 to the upper stage 121, a second stage 130 is connected in series by explosive bolts. The second stage 130 uses a solid-liquid hybrid rocket engine, and the upper stage 121 uses a solid rocket engine. The above method preferably further includes: after the solid-liquid hybrid rocket engine of the first stage 110 has been operating continuously for a period of time, the explosive bolt between the first stage 110 and the second stage 130 is activated, causing the first stage 110 and the second stage 130 to separate; 1 to 3 seconds (preferably 2 seconds) after the separation of the first stage 110 and the second stage 130, the solid-liquid hybrid rocket engine of the second stage 130 is ignited and operates, controlling the second stage 130 to correct its course; after entering the predetermined course, the solid-liquid hybrid rocket engine of the second stage 130 is shut down, and the explosive bolt between the second stage 130 and the upper stage 121 is activated, so that the upper stage 121 enters the gliding phase; after correcting the gliding trajectory of the upper stage 121, the solid rocket engine of the upper stage 121 is ignited to send the payload into the predetermined orbit in a three-axis stable attitude; after entering the predetermined orbit, the upper stage 121 releases the payload 101.

[0054] Depending on the actual size, payload requirements, and range of the launch vehicle, each stage of the launch vehicle can be configured with corresponding dimensions and power performance. As shown in the table below, this invention provides a specific embodiment of a solid-liquid hybrid launch vehicle and its launch method, incorporating a preferred embodiment.

[0055]

[0056] The solid-liquid hybrid launch vehicle is constructed from lightweight, high-strength composite materials. The solid rocket motor of booster 200 is preferably a solid rocket motor with thrust vector control using a swaying nozzle, with an engine diameter of 2.6 m, an average vacuum thrust of 2000 kN, and an burn time of 85 s. The solid-liquid hybrid rocket motors of first stage 110 and second stage 130 are preferably solid-liquid hybrid rocket motors with thrust vector control using swaying nozzles, both employing a combination of solid fuel and liquid oxidizer propellants. Specifically, the engine of first stage 110 has a diameter of 3 m, an average thrust of 1000 kN, and an burn time of 160 s. The engine of second stage 130 has a diameter of 3 m, an average vacuum thrust of 400 kN, and an burn time of 160 s. The upper stage 121 preferably has a solid rocket motor with thrust vector control using a swaying nozzle, an engine diameter of 2 m, an average vacuum thrust of 215 kN, and an burn time of 65 s.

[0057] The specific launch procedure for the solid-liquid hybrid launch vehicle described in the above embodiment is as follows:

[0058] The launch vehicle adopts a "three-horizontal testing and launch mode" of horizontal assembly, horizontal testing, and horizontal transportation. After being transported to the launch site by motor vehicle and erected, the launch vehicle is removed, the attitude is adjusted, and the launch is carried out.

[0059] After the launch vehicle is launched, the engines of booster 200 and first stage 110 reach a certain altitude and speed through the vertical takeoff phase, the programmed turn phase, and the zero angle of attack flight phase.

[0060] After 85 seconds of flight, the four boosters 200 shut down, and the separation rocket 210 and explosive bolts installed at the rear of the boosters 200 worked to separate the boosters 200 from the rocket.

[0061] When the solid-liquid hybrid rocket engine of the first stage 110 continued to work for 160 seconds, the explosive bolts installed on the interstage section of the first stage 110 and the second stage 130 were activated, and the first stage 110 and the second stage 130 separated by a small distance under the action of aerodynamic drag.

[0062] Two seconds after the first stage 110 separates, the solid-liquid hybrid rocket engine of the second stage 130 ignites and operates. The thrust generated by the nozzle 113 pushes the first stage 110 away, achieving thermal separation.

[0063] According to the pre-set plan, the rocket engine of the second stage 130 entered the programmed pitch angle flight state, and the ground control station implemented flight process monitoring and route correction through the launch vehicle / ground data link.

[0064] After the second stage 130 finishes its work, it is shut down. The explosive bolts in the interstage section of the second stage 130 and the upper stage 121 are engaged to achieve cold separation between the stages and enter the gliding stage.

[0065] During the gliding process, the attitude control engine 131 of the upper stage 121 starts to work and adjust the trajectory. After that, the solid rocket engine of the upper stage 121 ignites. At the same time, with the correction of the attitude control engine 131, the payload 101 is sent into the predetermined orbit in a three-axis stable attitude. The payload release mechanism releases the payload 101, completing all the work of the launch vehicle.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A solid-liquid hybrid launch vehicle, characterized in that, It includes the main body of the rocket (100) and multiple boosters (200); The rocket body (100) includes a first stage (110) located at the tail end and a fairing (120) located at the nose end. The payload (101) of the launch vehicle is disposed inside the fairing (120), and the booster (200) is installed on the first stage (110) by explosive bolts. The first stage (110) uses a hybrid rocket engine, and the booster (200) uses a solid rocket engine; The booster (200) is equipped with a separation rocket (210) that provides the power to move the booster (200) away from the first stage (110); The separation rocket (210) is associated with at least one of the explosive bolts so that the launch system of the separation rocket (210) can be triggered by unlocking the explosive bolts; The fairing (120) contains an upper stage (121), and the payload (101) is mounted on the upper stage (121). From the first stage (110) to the upper stage (121), a second stage (130) is connected in series by explosive bolts. The second stage (130) uses a solid-liquid hybrid rocket engine, and the upper stage (121) uses a solid rocket engine. The solid-liquid hybrid rocket engine includes an oxidizer tank (111), a solid fuel tank (112), and a nozzle (113). An electric pump delivery system is provided between the oxidizer tank (111) and the solid fuel tank (112). When the electric pump delivery system is not activated, the liquid oxidizer and solid fuel are stored in the oxidizer tank (111) and the solid fuel tank (112) respectively, forming a physically isolated state. When the electric pump delivery system is activated, the liquid oxidizer in the oxidizer tank is pressurized and delivered to the solid fuel tank (112). The solid fuel pyrolysis gas in the solid fuel tank (112) is mixed with the liquid oxidizer and combusted to provide propulsion power through the nozzle (113). The nozzle (113) is equipped with a thrust vector control system, which controls the flight trajectory of the launch vehicle during flight by controlling the swing angle of the nozzle (113).

2. The solid-liquid hybrid launch vehicle according to claim 1, characterized in that, The liquid oxidant includes one or more of nitric acid, liquid oxygen, nitrous oxide, and hydrogen peroxide; the solid fuel includes one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate, and paraffin.

3. The solid-liquid hybrid launch vehicle according to claim 1, characterized in that, The first stage (110), the second stage (130) and the upper stage (121) are provided with an attitude control system, which includes a plurality of attitude control engines (131) capable of providing radial power.

4. The solid-liquid hybrid launch vehicle according to any one of claims 1-3, characterized in that, The first stage (110) is pre-set with twelve mounting positions for mounting the boosters (200), and the number of boosters (200) on the launch vehicle is two, three, four, six or twelve.

5. The solid-liquid hybrid launch vehicle according to any one of claims 1-3, characterized in that, The tail end of the first stage (110) and / or the tail end of the booster (200) are provided with a heat-resistant protective cover (211).

6. A launch method for a solid-liquid hybrid launch vehicle, characterized in that, The method applied to the solid-liquid hybrid launch vehicle according to any one of claims 1-5 includes: After the launch preparations are completed, the solid rocket engine of the booster (200) and the solid-liquid hybrid rocket engine of the first stage (110) are started simultaneously. After a period of flight, the solid rocket motor of the booster (200) shuts down and the explosive bolts between the booster (200) and the first stage (110) are activated; Unlocking the explosive bolts triggers the launch system of the separation rocket (210), which provides power to move the booster (200) away from the first stage (110). The solid-liquid hybrid rocket engine of the first stage (110) continues to operate to propel the rocket body (100) into flight.

7. The launch method of the solid-liquid hybrid launch vehicle according to claim 6, characterized in that, The fairing (120) contains an upper stage (121), the payload (101) is mounted on the upper stage (121), and a second stage (130) is connected in series from the first stage (110) to the upper stage (121) by explosive bolts. The second stage (130) uses a solid-liquid hybrid rocket engine, and the upper stage (121) uses a solid rocket engine. The method includes: After the solid-liquid hybrid rocket engine of the first stage (110) has been working for a period of time, the explosive bolts between the first stage (110) and the second stage (130) are activated, causing the first stage (110) and the second stage (130) to separate. One to three seconds after the first stage (110) and the second stage (130) separate, the solid-liquid hybrid rocket engine of the second stage (130) ignites and controls the second stage (130) to correct its course. After entering the predetermined flight path, the solid-liquid hybrid rocket engine of the second stage (130) is shut down, and the explosive bolts between the second stage (130) and the upper stage (121) are activated to allow the upper stage (121) to enter the gliding phase. After correcting the glide trajectory of the upper stage (121), the solid rocket motor of the upper stage (121) is ignited to deliver the payload into the predetermined orbit in a triaxially stable attitude. After entering the predetermined orbit, the upper stage (121) releases the payload (101).

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