CN117589008A - Carrier rocket with solid-liquid hybrid power and launching method thereof - Google Patents

Abstract

The invention provides a carrier rocket of solid-liquid hybrid power and a launching method thereof, wherein the carrier rocket of the solid-liquid hybrid power comprises a rocket main body and a plurality of thrusters; the rocket main body comprises a sub-stage positioned at the tail end and a fairing positioned at the head end, the payload of the carrier rocket is arranged in the fairing, and the booster is arranged at the sub-stage through an explosion bolt; the first sub-stage adopts a solid-liquid hybrid rocket engine, and the booster adopts a solid rocket engine; the booster is provided with a separation rocket which can provide power for enabling the booster to be far away from the first sub-stage; the separation rocket is arranged in association with at least one explosion bolt so as to trigger a starting system of the separation rocket by unlocking the explosion bolt. The invention realizes a carrier rocket scheme which can ensure the commercial value and economic benefit of the carrier rocket and has quick response capability.

Description

Carrier rocket with solid-liquid hybrid power and launching method thereof

Technical Field

The invention relates to the technical field of aerospace, in particular to a carrier rocket of solid-liquid hybrid power and a launching method thereof.

Background

The carrier rocket is an aerospace carrier consisting of multiple rockets. Typically, a launch vehicle delivers payloads such as satellite vehicles, manned spacecraft, space stations, space probes, etc. into a predetermined orbit.

The common carrier rockets are classified into solid rockets, liquid rockets and the like according to the propellants used by the carrier rockets. For example, the carrier rocket of the third sign in China is a three-level liquid rocket; the carrier rocket of the first sign is a solid-liquid mixed three-stage rocket, wherein the first stage and the second stage are liquid rockets, and the third stage is a solid rocket; the carrier rocket of the flying horse seat in the United states is a three-stage solid rocket.

The liquid rocket engine has complex integral structure, and the propellant is unfavorable for storage and has corrosiveness and toxicity, inconvenient use and poor safety. The solid rocket engine has the advantages of simple structure, easy storage of propellant, mature technical development and high reliability, but the engine has lower specific impulse, relatively shorter working time, and difficult realization of thrust adjustment and repeated shutdown starting.

At present, aiming at the requirement of launching a small spacecraft, a carrier rocket with a quick response capability is urgently needed so as to achieve the purposes of preempting a first aircraft and quickly aiming at the carrier rocket in time, and the economic benefit of low cost is required to be paid attention to while the commercial value is considered. How to ensure the commercial value and economic benefit of the carrier rocket and also have the capability of quick response, is a technical problem which needs to be solved by the existing carrier rocket.

Disclosure of Invention

The invention provides a carrier rocket of solid-liquid hybrid power and a launching method thereof, which are used for solving the defect that the economic benefit and the response capability of the carrier rocket in the prior art are difficult to consider, and realizing a carrier rocket scheme which can ensure the commercial value and the economic benefit of the carrier rocket and has the rapid response capability.

The invention provides a carrier rocket of solid-liquid hybrid power, which comprises a rocket main body and a plurality of thrusters; the rocket main body comprises a sub-stage positioned at the tail end and a fairing positioned at the head end, the payload of the carrier rocket is arranged in the fairing, and the booster is arranged at the sub-stage through an explosion bolt; the first sub-stage adopts a solid-liquid hybrid rocket engine, and the booster adopts a solid rocket engine; the booster is provided with a separation rocket which can provide power for enabling the booster to be far away from the first sub-stage; the separation rocket is arranged in association with at least one explosion bolt so as to trigger a starting system of the separation rocket by unlocking the explosion bolt.

According to the carrier rocket of the solid-liquid hybrid power, the upper stage is arranged in the fairing, the effective load is arranged on the upper stage, and the two sub-stages are connected in series through the explosion bolt from the first sub-stage to the upper stage; the second sub-stage adopts a solid-liquid hybrid rocket engine, and the upper stage adopts a solid rocket engine.

According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the solid-liquid hybrid rocket engine comprises an oxidant tank, a solid fuel tank and a spray pipe; an electric pump conveying system is arranged between the oxidant tank and the solid fuel tank; when the electric pump conveying system is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant tank and the solid fuel tank to form a physical isolation state; when the electric pump conveying system is started, the liquid oxidant in the oxidant tank is pressurized and conveyed to the solid fuel tank, and the solid fuel pyrolysis gas in the solid fuel tank is mixed with the liquid oxidant for combustion so as to provide propulsion power through the spray pipe.

According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the liquid oxidant comprises one or more of nitric acid, liquid oxygen, nitrous oxide and hydrogen peroxide; the solid fuel comprises one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate and paraffin.

According to the carrier rocket of the solid-liquid hybrid power, the jet pipe is provided with the thrust vector control system, and the thrust vector control system controls the flying trajectory of the carrier rocket in the flying process by controlling the swing angle of the jet pipe.

According to the carrier rocket of the solid-liquid hybrid power, provided by the invention, the first sub-stage, the second sub-stage and the upper stage are provided with the attitude control system, and the attitude control system comprises a plurality of attitude control engines capable of providing radial power.

According to the carrier rocket of the solid-liquid hybrid power, twelve mounting positions for mounting the thrusters are preset in one sub-stage, and the number of the thrusters on the carrier rocket is two, three, four, six or twelve.

According to the carrier rocket of the solid-liquid hybrid power, provided by the invention, the tail end of the first sub-stage and/or the tail end of the booster is provided with a protective cover made of heat-resistant materials.

The invention also provides a launch method of the carrier rocket of the solid-liquid hybrid power, which is applied to any carrier rocket of the solid-liquid hybrid power, and comprises the following steps: after the preparation work of launching is finished, simultaneously starting a solid rocket engine of the booster and the solid-liquid hybrid rocket engine of the first sub-stage; after flying for a period of time, the solid rocket engine of the booster is shut down, and an explosion bolt between the booster and the first sub-stage is started; triggering a starting system of the separation rocket through unlocking of the explosion bolt, wherein the separation rocket provides power so as to enable the booster to be far away from the first sub-stage; and the solid-liquid hybrid rocket engine of the first sub-stage continuously works so as to push the rocket main body to continuously fly.

According to the launch method of the carrier rocket of the solid-liquid hybrid power, provided by the invention, the upper stage is arranged in the fairing, the payload is arranged on the upper stage, and two sub-stages are connected in series from the first sub-stage to the upper stage through explosion bolts, wherein the two sub-stages adopt solid-liquid hybrid rocket engines, and the upper stage adopts solid rocket engines; the method comprises the following steps: after the solid-liquid hybrid rocket engine of the first sub-stage continuously works for a period of time, an explosion bolt between the first sub-stage and the second sub-stage is started to separate the first sub-stage from the second sub-stage; after the first sub-stage and the second sub-stage are separated for 1 to 3 seconds, the solid-liquid hybrid rocket engine of the second sub-stage is ignited to work, and the second sub-stage corrected route is controlled; after entering a preset route, the solid-liquid hybrid rocket engine of the second sub-stage is shut down, and an explosion bolt between the second sub-stage and the upper stage is started so that the upper stage enters a gliding stage; after correcting the glide orbit of the upper stage, the solid rocket engine of the upper stage is ignited to send the effective load into a preset orbit in a triaxial stable posture; upon entering the predetermined track, the upper stage releases the payload.

According to the carrier rocket of the solid-liquid hybrid power and the launching method thereof, the first sub-stage of the solid-liquid hybrid rocket engine and the booster of the solid rocket engine are adopted to work simultaneously in the starting stage of the carrier rocket, the booster of the solid rocket engine has a faster response speed, sufficient acceleration can be provided for the carrier rocket in a short time, the first sub-stage of the solid-liquid hybrid rocket engine takes the advantages of the traditional solid rocket engine and the liquid rocket engine into consideration, the safety is high, and the maintenance guaranteeing cost is reduced. In addition, the separation rocket can provide power for enabling the booster to be far away from the first sub-stage, and in the separation process of the booster and the first sub-stage, the success rate of separation can be improved, and further loss of emission failure is reduced.

Drawings

In order to more clearly illustrate the invention or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of a solid-liquid hybrid launch vehicle according to the present invention;

fig. 2 is a schematic structural diagram of a mounting relationship between a sub-stage of a solid-liquid hybrid carrier rocket and a booster provided by the invention.

Reference numerals:

100: a rocket body; 101: a payload; 110: a sub-stage; 111: an oxidant tank; 112: a solid fuel tank; 113: a spray pipe; 120: a fairing; 121: an upper stage; 130: a second sub-stage; 131: a gesture control engine; 200: a booster; 210: separating the rocket; 211: and a protective cover.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

Rocket engines are the most important components in a launch vehicle. Currently, rocket engines with a relatively large number of practical applications can be divided into three types: liquid rocket engines, solid rocket engines, and solid-liquid hybrid rocket engines. The liquid rocket engine widely applied in the field of aerospace transportation has high fuel energy density, high specific impulse, easy realization of flow control and thrust regulation, capability of being started by multiple times of shutdown, complex integral structure, difficult storage of propellant, multiple corrosivity and toxicity, inconvenient use and poor safety; the solid rocket engine has the advantages that the structure is simple, the propellant is easy to store, the technology is developed and mature, the reliability is high, but the specific impulse of the engine is low, the working time is relatively short, and the thrust adjustment and repeated shutdown starting are difficult to realize; the solid-liquid hybrid rocket engine has the advantages of high specific impulse, adjustable thrust, capability of being started by multiple times of shutdown, easiness in storage, simple structure, high reliability and low maintenance cost, and has excellent economic performance and good application prospect.

The invention provides a carrier rocket of solid-liquid hybrid power by cooperatively matching a solid rocket engine and a solid-liquid hybrid rocket engine, which fully utilizes the advantages of the solid rocket engine and the solid-liquid hybrid rocket engine, and realizes a carrier rocket scheme with quick response capability while ensuring the commercial value and economic benefit of the carrier rocket.

A solid-liquid hybrid launch vehicle according to a preferred embodiment of the present invention is described below with reference to fig. 1.

As shown in FIG. 1, rocket body 100 includes a first sub-stage 110, a second sub-stage 130, and an upper stage 121, which are sequentially connected in series from the tail end to the head end. Both the first sub-stage 110 and the second sub-stage 130 employ a solid-liquid hybrid rocket engine including an oxidizer tank 111, a solid fuel tank 112, and a nozzle 113 with a thrust vectoring system. The upper stage 121 employs a solid rocket engine, the upper stage 121 being fitted with a payload 101, the exterior of which is provided with a fairing 120. Around one sub-stage 110 is bundled a booster 200 of a solid rocket engine. The first sub-stage 110, the second sub-stage 130 and the fairing 120, and the first sub-stage 110 and the booster 200 are all mounted by explosive bolts. The booster 200 is further provided with a separation rocket 210 to trigger a starting system of the separation rocket 210 after the explosion bolt is started and unlocked, and the booster 200 is quickly separated from the sub-stage 110 by power provided by the separation rocket 210. The separating rocket 210 is preferably arranged at the tail end of the booster 200, and the tail end of the first sub-stage 110 and/or the tail end of the booster 200 is/are preferably provided with a protective cover 211 made of heat-resistant materials, so that on one hand, the temperature tolerance to rocket tail inflammation is improved, and on the other hand, the damage to the first sub-stage 110 after the separating rocket 210 is started can be prevented.

After the launch preparation of the solid-liquid hybrid launch vehicle of the preferred embodiment is completed, the solid rocket engine of the booster 200 and the solid-liquid hybrid rocket engine of the first sub-stage 110 are started simultaneously, so that the quick response capability of the solid rocket engine is utilized to enable the launch vehicle to achieve the acceleration requirement of take-off more quickly. After a period of flight, the solid rocket engine of booster 200 is shut down and the explosive bolts between booster 200 and a sub-stage 110 are activated, and the explosive bolts unlock, triggering the activation system of split rocket 210, igniting split rocket 210 to provide power to move booster 200 away from a sub-stage 110. By separating the rocket 210, the separation action of the booster 200 and the sub-stage 110 is more thorough, so that the collision risk in the separation process can be reduced, the rocket launching success rate is improved, and the loss caused by the launching failure is further reduced.

The solid-liquid hybrid rocket engine is adopted according to the power of the first sub-stage 110 and the second sub-stage 130, and the liquid oxidant is physically isolated from the solid fuel before ignition, so that the safety is high, and the maintenance cost is reduced; the power system of the upper stage 121 and the booster 200 adopts a solid rocket engine, so that the thrust is large, the mass ratio is high, and the carrier rocket scale is effectively reduced under the condition of transporting payloads with the same mass, the flight time is shortened, and the quick response capability is improved.

In order to better understand the above technical solution, the solid-liquid hybrid carrier rocket and the launching method thereof according to the present invention will be described in detail with reference to specific embodiments.

The carrier rocket of the solid-liquid hybrid power provided by the invention comprises a rocket main body 100 and a plurality of thrusters 200; rocket body 100 includes a sub-stage 110 at the tail end and a fairing 120 at the head end, payload 101 of the launch vehicle is disposed within fairing 120, booster 200 is mounted to sub-stage 110 by an explosive bolt; a sub-stage 110 adopts a solid-liquid hybrid rocket engine, and a booster 200 adopts a solid rocket engine; booster 200 is provided with a separation rocket 210, separation rocket 210 being capable of providing power to move booster 200 away from one sub-stage 110; the separation rocket 210 is provided in association with at least one explosion bolt so that a starting system of the separation rocket 210 can be triggered by unlocking the explosion bolt. Wherein each booster 200 is preferably connected to a sub-stage 110 by a plurality of explosive bolts that are simultaneously unlocked during the separation process. After the explosion bolts are unlocked, the rocket-borne computer of the carrier rocket sends an ignition command to the starting system of the separation rocket 210 in real time, and the starting system of the separation rocket 210 can be set to be started in real time by ignition or delayed for 0 to 1 second after receiving the command to ensure that the explosion bolts between the booster 200 and the sub-stage 110 are fully unlocked and disconnected when the separation rocket 210 is started. The fairing 120 preferably has a cone shape that breaks open air as a protection mechanism for the payload 101.

The booster 200 of the solid rocket engine has a faster response speed, can provide sufficient acceleration for the carrier rocket in a short time, and the solid-liquid hybrid rocket engine of the first sub-stage 110 takes advantages of the traditional solid rocket engine and the traditional liquid rocket engine into consideration, so that the safety is high, and the maintenance guaranteeing cost is reduced. Moreover, the separation rocket 210 can provide power for separating the booster 200 from the first sub-stage 110, and the success rate of separation can be improved during the separation process of the booster 200 and the first sub-stage 110, so as to reduce the loss of emission failure.

The separation rocket 210 arranged in association with at least one explosion bolt can be replaced by a high-pressure gas container besides a chemical energy rocket in a combustion form. The sensor circuit can be used for detecting the state of the explosion bolt to start the starting system of the separation rocket 210; or the state of the explosion bolt is monitored by an rocket-borne computer of the carrier rocket, and when the explosion bolt is unlocked, a starting instruction is sent to a starting system of the separation rocket 210. After the start system of the separation rocket 210 receives the start command, the start task of the separation rocket 210 is executed immediately or delayed, and according to different types of the separation rocket 210, chemical fuel in the separation rocket 210 is ignited, or high-pressure gas is released, so that a force for enabling the booster 200 to be far away from the carrier rocket in the radial direction is generated.

According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the carrier rocket can be set as a primary carrier rocket, a secondary carrier rocket or a multi-stage carrier rocket according to requirements. Preferably, as shown in fig. 1, an upper stage 121 is provided in the fairing 120, the payload 101 is mounted on the upper stage 121, and a second sub-stage 130 is connected in series between the first sub-stage 110 and the upper stage 121 through explosion bolts; the second sub-stage 130 employs a solid-liquid hybrid rocket motor, and the upper stage 121 employs a solid rocket motor.

Preferably, the upper stage 121 is provided with a payload separation mechanism and is connected to the rest of the launch vehicle by a pod. After the upper stage 121 enters the predetermined track, the payload may be released by a payload separation mechanism. The explosion bolts among the mechanisms of the carrier rocket can be any one or more of slotted type, shearing pin type, steel ball type explosion bolts, pollution-free explosion bolts and the like.

The carrier rocket of the solid-liquid hybrid power at least comprises: in the takeoff phase, a sub-stage 110 and the booster 200 are started simultaneously; the first separation, the booster 200 is separated from the carrier rocket, and the power is continuously output by the first sub-stage 110; the second separation, the first sub-stage 110 is separated, and the solid-liquid hybrid rocket engine of the second sub-stage 130 outputs power; the third separation, the second sub-stage 130 is disengaged and the solid rocket engine of the upper stage 121 pushes the payload 101 to a predetermined orbit in response to the start-up.

According to the characteristics of the solid-liquid hybrid rocket engine and the solid rocket engine, the first sub-stage 110 and the second sub-stage 130 of the carrier rocket have the advantages of high engine specific impulse, adjustable thrust, capability of being started by multiple shutdown, easiness in storage of the solid rocket engine, simple structure, high reliability and low maintenance cost; the booster 200 and the upper stage 121 have large thrust and high mass ratio, and have small scale requirement and short flight time consumption under the condition of transporting the same mass load, and have higher quick response capability. Wherein, the solid rocket engine of the upper stage 121 has high mass ratio, large thrust and capacity of improving quick response capability by reducing the scale of the fairing 120 and shortening the flight time of the carrier rocket in the orbit stage under the condition of transporting the payload 101 with the same mass.

According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the solid-liquid hybrid rocket engine comprises an oxidant tank 111, a solid fuel tank 112 and a spray pipe 113; an electric pump delivery system is provided between the oxidizer tank 111 and the solid fuel tank 112. When the electric pump conveying system is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant tank 111 and the solid fuel tank 112 to form a physical isolation state; when the electric pump delivery system is started, the liquid oxidant in the oxidant tank is pressurized and delivered to the solid fuel tank 112, and the solid fuel pyrolysis gas in the solid fuel tank 112 is mixed with the liquid oxidant for combustion, so as to provide propulsion power through the spray pipe 113.

The electric pump conveying system has the advantages of low cost, simple system, low storage tank pressure, light structural weight, large variable thrust range, flexible working mode and the like. The combustion power of the solid-liquid hybrid rocket engine can be regulated in real time by controlling the conveying power of the liquid oxidant through the electric pump conveying system, so that the thrust of the carrier rocket can be regulated easily. Under the condition that the electric pump conveying system is stopped, physical isolation is formed between the liquid oxidant and the solid fuel which are respectively stored in the oxidant tank 111 and the solid fuel tank 112, the electric pump conveying system is high in safety and brand new, and the starting and stopping of the solid-liquid hybrid rocket engine can be controlled at any time by controlling the electric pump conveying system, so that the carrier rocket can adapt to more complex flight environments.

According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the liquid oxidant can be liquid oxygen liquid fluorine, liquid nitrous oxide, hydrogen peroxide, nitric acid and the like, and preferably comprises one or more of nitric acid, liquid oxygen, nitrous oxide and hydrogen peroxide. The solid fuel mainly comprises a polymeric compound, a metal hydride and the like, and preferably comprises one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate and paraffin.

According to the carrier rocket of the solid-liquid hybrid power, the jet pipe 113 is provided with the thrust vector control system, and the thrust vector control system controls the flight trajectory of the carrier rocket in the flight process by controlling the swing angle of the jet pipe 113.

Nozzle 113 may be a flexible nozzle or a ball and socket nozzle. It will be appreciated that in the present invention, the nozzle 113 described above can be used not only with solid-liquid hybrid rocket engines of the first and second sub-stages 110 and 130, but also with solid rocket engines of the booster 200 and the upper stage 121. At any stage in the carrier rocket flight process, the swing angle can be adjusted through the control tube 113 of the thrust vector control system, so that the flight trajectory of the carrier rocket can be flexibly regulated and controlled at any time.

In addition, the solid-liquid hybrid launch vehicle of the present invention may also control the attitude of the vehicle by other means, such as providing a secondary fluid injection system at the nozzle 113 of the rocket engine to inject liquid or gaseous fluid into the engine jet through the nozzle diffuser. The injected fluid creates a shock wave in the supersonic jet stream causing an imbalance in the pressure distribution, thereby deflecting the stream.

According to the solid-liquid hybrid carrier rocket provided by the invention, the first sub-stage 110, the second sub-stage 130 and the upper stage 121 can also be provided with a posture control system, and the posture control system comprises a plurality of posture control engines 131 capable of providing radial power.

As shown in fig. 1, the above-mentioned attitude control engine 131 may be provided in an inter-stage section between the first sub-stage 110 and the second sub-stage 130, and when the attitude control engine 131 is started, the air flow is injected toward the radial direction of the carrier rocket, thereby providing power for adjusting the flight attitude of the carrier rocket in the radial direction of the carrier rocket. In practical applications, the number of the attitude control engines 131 is preferably plural, and the plurality of attitude control engines 131 may be disposed on the first sub-stage 110, the second sub-stage 130 and the upper stage 121 of the carrier rocket or on any stage section between the first sub-stage 110, the second sub-stage 130 and the upper stage 121 according to the launching requirement. Preferably, the first sub-stage 110 and the second sub-stage 130 are respectively provided with four attitude control engines 131, and the upper stage 121 is provided with at least six attitude control engines 131 so as to respectively cope with attitude control requirements of the carrier rocket when in lift-off and track-on.

Specifically, the control system of the preferred embodiment may include helium cylinders, high pressure valves, filters, pressure reducing valves, solenoid valves, and a control thrust chamber to make up the control engine 131. The helium bottle is connected with the filter through the high-pressure valve, the other end of the filter is provided with the relief pressure valve, one end of the relief pressure valve, which is far away from the filter, is provided with the electromagnetic valve, and one end of the electromagnetic valve, which is far away from the relief pressure valve, is provided with the attitude control thrust chamber. By releasing the high pressure helium in the helium cylinder, a jet stream is formed that provides radial motive force.

According to the carrier rocket with solid-liquid hybrid power provided by the invention, on the basis of the carrier rocket in any embodiment, according to different carrying targets of the carrier rocket, different numbers of the thrusters 200 can be adopted, and the initial acceleration with quick response can be provided in the initial flight stage of the carrier rocket.

Preferably, as shown in fig. 2, twelve mounting positions for mounting the boosters 200 are preset in one sub-stage 110, and a worker can timely install a corresponding number of boosters 200 on one sub-stage 110 in the preparation stage of the carrier rocket according to actual carrying requirements. The number of the boosters 200 on the carrier rocket can be two, three, four, six or twelve.

Further, during more complex flight conditions, the plurality of boosters 200 can be activated in batches, so that the booster 200 can be used to provide boosting during flight phases other than the initial take-off phase. For example, four boosters have been provided, two of the four boosters 200 are relatively distributed to be started simultaneously with one sub-stage 110 in the working time period of the solid-liquid hybrid rocket engine of the sub-stage 110, and the other two boosters 200 are started when the two boosters 200 started in the first batch are stopped, so as to prolong the working time of the boosters 200.

According to the solid-liquid hybrid carrier rocket provided by the invention, the tail end of one sub-stage 110 and/or the tail end of the booster 200 is provided with a protective cover 211 made of heat-resistant materials. On the one hand, the protective cover 211 can improve the capability of the tail end of the sub-stage 110 and/or the tail end of the booster 200 to resist the tail inflammatory temperature of the carrier rocket, on the other hand, the separation rocket 210 of the booster 200 is preferably arranged at the tail end of the booster 200, and when the separation rocket 210 is started, the protective cover 211 on the sub-stage 110 can isolate the high-temperature gas ejected by the separation rocket 210 to prevent the separation rocket 210 from damaging the sub-stage 210.

Based on the solid-liquid hybrid power carrier rocket, the invention provides a method for launching the carrier rocket applied to the solid-liquid hybrid power, which comprises the following steps: after the preparation work of launching is completed, the solid rocket engine of the booster 200 and the solid-liquid hybrid rocket engine of the sub-stage 110 are started simultaneously; after a period of flight, the solid rocket engine of booster 200 is shut down and an explosive bolt between booster 200 and a sub-stage 110 is started; by unlocking the explosive bolt, triggering the starting system of the separation rocket 210, the separation rocket 210 providing power to move the booster 200 away from the one sub-stage 110; the solid-liquid hybrid rocket engine of one sub-stage 110 continues to operate to propel the rocket body 100 to continue flying.

The solid rocket engine of the booster 200 can quickly respond in the starting stage, and provides a large amount of boosting power for the carrier rocket in a short time, so that after the power output of the solid-liquid hybrid rocket engine of the sub-stage 110 is combined, the carrier rocket can obtain enough take-off acceleration in a short time. When the booster 200 is separated, the separation rocket 210 is triggered by unlocking the explosion bolt, and power for reliably separating the booster 200 from the first sub-stage 110 is provided, so that accidental collision in the separation process can be prevented, and the separation success rate is improved.

An upper stage 121 is arranged in a fairing 120 of a carrier rocket according to solid-liquid hybrid power, a payload 101 is arranged on the upper stage 121, a second stage 130 is connected in series from a first stage 110 to the upper stage 121 through explosion bolts, the second stage 130 adopts a solid-liquid hybrid rocket engine, and the upper stage 121 adopts a solid rocket engine. The above method preferably further comprises: after the solid-liquid hybrid rocket engine of the first sub-stage 110 continuously works for a period of time, an explosion bolt between the first sub-stage 110 and the second sub-stage 130 is started, so that the first sub-stage 110 and the second sub-stage 130 are separated; after the first sub-stage 110 and the second sub-stage 130 are separated for 1 to 3 seconds (preferably 2 seconds), the solid-liquid hybrid rocket engine of the second sub-stage 130 operates in an ignition mode, and the second sub-stage 130 is controlled to correct the route; after entering a preset route, the solid-liquid hybrid rocket engine of the second sub-stage 130 is shut down, and an explosion bolt between the second sub-stage 130 and the upper stage 121 is started, so that the upper stage 121 enters a gliding stage; after correcting the glide trajectory of the upper stage 121, the solid rocket engine of the upper stage 121 is ignited to deliver the payload in a three-axis stable posture into a predetermined trajectory; upon entering the predetermined track, the upper stage 121 releases the payload 101.

Based on the actual scale, carrying requirement, sailing distance and other aspects of the carrier rocket, the structures of each stage of the carrier rocket can be respectively provided with corresponding size and dynamic performance. As shown in the following table, the present invention provides a specific example in combination with the solid-liquid hybrid launch vehicle and the launching method thereof according to the preferred embodiment.

Each part of the carrier rocket of the solid-liquid hybrid power is made of a light high-strength composite material. The solid rocket engine of booster 200 is preferably a solid rocket engine using a swing nozzle for thrust vectoring control, the engine diameter being 2.6m, the vacuum average thrust being 2000kN, and the operating time being 85s. The solid-liquid hybrid rocket engines of the first sub-stage 110 and the second sub-stage 130 are preferably solid-liquid hybrid rocket engines using oscillating nozzles for thrust vectoring, each employing a propellant combination of solid fuel and liquid oxidizer. Wherein the engine diameter of one sub-stage 110 is 3m, the average thrust of the working process is 1000kN, and the working time is 160s. The engine diameter of the second sub-stage 130 is 3m, the vacuum average thrust is 400kN, and the working time is 160s. The upper stage 121 preferably has a solid rocket engine with thrust vectoring using a swing nozzle, an engine diameter of 2m, a vacuum average thrust of 215kN, and an operating time of 65s.

The specific launching flow of the solid-liquid hybrid power carrier rocket in the embodiment is as follows:

the carrier rocket adopts a three-level test launch mode of horizontal assembly, horizontal test and horizontal transportation, and is launched by a motor vehicle after being transported to a launch point and erected, the launch vehicle is evacuated, and the posture is adjusted.

After launch of the launch vehicle, the booster 200 and the engines of the sub-stage 110 reach altitude and speed via a vertical takeoff segment, a programmed turn phase, and a zero angle of attack flight segment.

After the four thrusters 200 are shut down after the flying for 85 seconds, a separation rocket 210 and an explosion bolt mounted at the rear of the thrusters 200 work to separate the thrusters 200 from the rocket.

When the solid-liquid hybrid rocket engine of the first sub-stage 110 continues to operate for 160 seconds, the explosive bolts mounted on the interstage sections of the first sub-stage 110 and the second sub-stage 130 operate, and the first sub-stage 110 and the second sub-stage 130 are separated by a small distance under the action of aerodynamic drag.

After the first sub-stage 110 is separated for 2 seconds, the solid-liquid hybrid rocket engine of the second sub-stage 130 operates in an ignition mode, and thrust generated by the spray pipe 113 pushes the first sub-stage 110 away to realize thermal separation.

According to a preset scheme, the rocket engine of the second sub-stage 130 enters a program pitch angle flight state, and the ground control station implements flight process monitoring and route correction through a carrier rocket/ground data link.

After the second sub-stage 130 is finished, the engine is shut down, and explosion bolts of the inter-stage sections of the second sub-stage 130 and the upper stage 121 work to realize inter-stage cold separation and enter a gliding section.

The attitude control engine 131 of the upper stage 121 starts to work to adjust the orbit in the gliding process, the solid rocket engine of the upper stage 121 ignites after the completion, meanwhile, the effective load 101 is sent into a preset orbit in a triaxial stable attitude under the correction of the attitude control engine 131, and the effective load 101 is released by the effective load releasing mechanism, so that the whole work of the carrier rocket is completed.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims (10)

1. A carrier rocket of solid-liquid hybrid power, which is characterized by comprising a rocket main body (100) and a plurality of thrusters (200);

the rocket main body (100) comprises a sub-stage (110) positioned at the tail end and a fairing (120) positioned at the head end, a payload (101) of the carrier rocket is arranged in the fairing (120), and the booster (200) is mounted on the sub-stage (110) through an explosion bolt;

the first sub-stage (110) adopts a solid-liquid hybrid rocket engine, and the booster (200) adopts a solid rocket engine;

the booster (200) is provided with a separation rocket (210), the separation rocket (210) being capable of providing power to move the booster (200) away from the one sub-stage (110);

the separating rocket (210) is associated with at least one of the explosion bolts, so that a starting system of the separating rocket (210) can be triggered by unlocking the explosion bolt.

2. A solid-liquid hybrid launch vehicle according to claim 1, characterized in that an upper stage (121) is provided in the fairing (120), the payload (101) is mounted on the upper stage (121), and two sub-stages (130) are connected in series between the first sub-stage (110) and the upper stage (121) through explosion bolts;

the second sub-stage (130) adopts a solid-liquid hybrid rocket engine, and the upper stage (121) adopts a solid rocket engine.

3. A solid-liquid hybrid launch vehicle according to claim 2, wherein the solid-liquid hybrid rocket engine comprises an oxidizer tank (111), a solid fuel tank (112) and a nozzle (113);

an electric pump delivery system is arranged between the oxidant tank (111) and the solid fuel tank (112);

when the electric pump conveying system is not started, liquid oxidant and solid fuel are respectively stored in the oxidant tank (111) and the solid fuel tank (112) to form a physical isolation state;

when the electric pump conveying system is started, the liquid oxidant in the oxidant tank is pressurized and conveyed to the solid fuel tank (112), and the solid fuel pyrolysis gas in the solid fuel tank (112) is mixed with the liquid oxidant for combustion so as to provide propulsion power through the spray pipe (113).

4. A solid-liquid hybrid launch vehicle according to claim 3, wherein the liquid oxidizer comprises one or more of nitric acid, liquid oxygen, nitrous oxide, hydrogen peroxide; the solid fuel comprises one or more of polyethylene, hydroxyl-terminated polybutadiene, polymethyl methacrylate and paraffin.

5. A solid-liquid hybrid launch vehicle according to claim 3, characterized in that the nozzle (113) is provided with a thrust vectoring system for controlling the trajectory of the launch vehicle during flight by controlling the oscillation angle of the nozzle (113).

6. A solid-liquid hybrid launch vehicle according to claim 2, characterized in that the first sub-stage (110), the second sub-stage (130) and the upper stage (121) are provided with a attitude control system comprising a plurality of attitude control engines (131) capable of providing radial power.

7. A solid-liquid hybrid vehicle according to any of claims 1-6, characterized in that twelve mounting locations for mounting the thrusters (200) are preset for the one sub-stage (110), the number of thrusters (200) on the vehicle being two, three, four, six or twelve.

8. A solid-liquid hybrid launch vehicle according to any one of claims 1 to 6, characterized in that the tail end of the first sub-stage (110) and/or the tail end of the booster (200) is provided with a protective cover (211) of heat resistant material.

9. A method for launching a solid-liquid hybrid launch vehicle, applied to the solid-liquid hybrid launch vehicle of any one of claims 1-8, the method comprising:

after the preparation work of launching is finished, simultaneously starting a solid rocket engine of the booster (200) and a solid-liquid hybrid rocket engine of the first sub-stage (110);

after a period of flight, the solid rocket engine of the booster (200) is shut down, and an explosive bolt between the booster (200) and the sub-stage (110) is started;

triggering a starting system of the separation rocket (210) through unlocking of the explosion bolt, wherein the separation rocket (210) provides power to enable the booster (200) to be far away from the sub-stage (110);

the solid-liquid hybrid rocket engine of the first sub-stage (110) continues to work so as to push the rocket body (100) to continue flying.

10. The method for launching a solid-liquid hybrid launch vehicle according to claim 9, wherein an upper stage (121) is provided in said fairing (120), said payload (101) is mounted on said upper stage (121), and two sub-stages (130) are connected in series between said first sub-stage (110) and said upper stage (121) through explosion bolts, said two sub-stages (130) being solid-liquid hybrid rocket engines, said upper stage (121) being solid rocket engines;

the method comprises the following steps:

after the solid-liquid hybrid rocket engine of the first sub-stage (110) continuously works for a period of time, an explosion bolt between the first sub-stage (110) and the second sub-stage (130) is started, so that the first sub-stage (110) and the second sub-stage (130) are separated;

after the first sub-stage (110) and the second sub-stage (130) are separated for 1 to 3 seconds, the solid-liquid hybrid rocket engine of the second sub-stage (130) operates in an ignition mode, and the second sub-stage (130) is controlled to correct the route;

after entering a preset route, the solid-liquid hybrid rocket engine of the second sub-stage (130) is shut down, and an explosion bolt between the second sub-stage (130) and the upper stage (121) is started so that the upper stage (121) enters a gliding stage;

after correcting the glide trajectory of the upper stage (121), the solid rocket engine of the upper stage (121) is ignited to feed the payload into a predetermined trajectory in a three-axis stable posture;

upon entering the predetermined track, the upper stage (121) releases the payload (101).