CN116929159B - Carrier rocket with solid-liquid hybrid power and launching method thereof - Google Patents
Carrier rocket with solid-liquid hybrid power and launching method thereof Download PDFInfo
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- CN116929159B CN116929159B CN202311198779.8A CN202311198779A CN116929159B CN 116929159 B CN116929159 B CN 116929159B CN 202311198779 A CN202311198779 A CN 202311198779A CN 116929159 B CN116929159 B CN 116929159B
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- 239000007788 liquid Substances 0.000 title claims abstract description 134
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- 230000001590 oxidative effect Effects 0.000 claims description 36
- 238000003860 storage Methods 0.000 claims description 22
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 239000007789 gas Substances 0.000 claims description 13
- 239000007921 spray Substances 0.000 claims description 13
- 239000012530 fluid Substances 0.000 claims description 7
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 claims description 6
- 239000004698 Polyethylene Substances 0.000 claims description 6
- 229920003229 poly(methyl methacrylate) Polymers 0.000 claims description 6
- 239000004926 polymethyl methacrylate Substances 0.000 claims description 6
- 238000012546 transfer Methods 0.000 claims description 6
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- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 3
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical group O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 229910017604 nitric acid Inorganic materials 0.000 claims description 3
- 239000012188 paraffin wax Substances 0.000 claims description 3
- -1 polyethylene Polymers 0.000 claims description 3
- 229920000573 polyethylene Polymers 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 238000009792 diffusion process Methods 0.000 claims description 2
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- 230000008901 benefit Effects 0.000 abstract description 22
- 238000012423 maintenance Methods 0.000 abstract description 9
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0406—Rail launchers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to the technical field of aerospace, and 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 the following components: a first sub-stage, a second sub-stage, an upper stage, a fairing and a plurality of boost stages; wherein, the first sub-stage, the second sub-stage and the upper stage are connected in sequence in a separable way, the upper stage is internally provided with a payload, the fairing covers the outside of the upper stage, and a plurality of boosting stages are connected on the side surface of the first sub-stage in a separable way; the first sub-stage, the second sub-stage and the boosting stage adopt solid-liquid mixed rocket engines, and liquid oxidants and solid fuels are adopted in the solid-liquid mixed rocket engines; the upper stage adopts a liquid rocket engine. By adopting solid-liquid hybrid rocket engines as main power systems in the boosting stage, the first sub-stage and the second sub-stage, the carrier rocket has the advantages of high specific impulse, adjustable thrust, high reliability and low maintenance cost, and can have quick response capability and reduce the cost at the same time, thereby ensuring the commercial value and economic benefit of the carrier rocket.
Description
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. In general, a carrier rocket may be used to transport payloads of man-made earth satellites, manned spacecraft, space stations, space probes, etc. into a predetermined orbit.
The most important component in a launch vehicle is the rocket engine. Currently, rocket engines with a relatively large number of practical applications can be divided into two categories: liquid rocket engines and solid rocket engines. The liquid rocket engine has high fuel energy density and specific impulse, is easy to realize flow control and thrust adjustment, and can be started by shutdown for multiple times, so that the liquid rocket engine is widely applied to the field of aerospace transportation. However, the whole structure is complex, the propellant is not easy to store and has corrosiveness and toxicity, the use is inconvenient, and the safety is poor. 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.
Therefore, rockets formed by liquid rocket engines or solid rocket engines cannot have quick response capability and simultaneously reduce cost, so that the commercial value and the economic benefit of the rockets are ensured.
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 defects that in the prior art, no matter a rocket formed by adopting a liquid rocket engine or a solid rocket engine can not have quick response capability and simultaneously reduce cost, thereby ensuring commercial value and economic benefit of the rocket, and realizing the advantages of high specific impulse, adjustable thrust, capability of being started by shutting down for multiple times, easiness in storage of the solid rocket engine, simple structure, high reliability and low guarantee of maintenance cost, and can have quick response capability and simultaneously reduce cost, thereby ensuring the commercial value and the economic benefit of the carrier rocket.
The invention provides a carrier rocket of solid-liquid hybrid power, comprising: a first sub-stage, a second sub-stage, an upper stage, a fairing and a plurality of boost stages;
the auxiliary power generation system comprises a first sub-stage, a second sub-stage and an upper stage, wherein the first sub-stage, the second sub-stage and the upper stage are sequentially and detachably connected, a payload is arranged in the upper stage, the fairing is arranged outside the upper stage, and a plurality of auxiliary power generation stages are detachably connected to the side face of the first sub-stage;
the first sub-stage, the second sub-stage and the boosting stage are all solid-liquid hybrid rocket engines, and liquid oxidants and solid fuels are adopted in the solid-liquid hybrid rocket engines;
the upper stage adopts a liquid rocket engine.
According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the liquid oxidant adopted in the solid-liquid hybrid rocket engine is physically isolated from the solid fuel before ignition.
According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the solid-liquid hybrid rocket engine comprises a gas generator, an oxidant storage tank, a delivery pump and a solid fuel tank;
the gas generator and the delivery pump are both fixedly disposed between the oxidizer storage tank and the solid fuel tank.
According to the carrier rocket of the solid-liquid hybrid power, the solid-liquid hybrid rocket engine further comprises an engine thrust chamber and a spray pipe, wherein the engine thrust chamber is used for controlling the spray pipe by adopting thrust vectors.
According to the carrier rocket of the solid-liquid hybrid power provided by the invention,
when the delivery pump is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant storage tank and the solid fuel tank to form a physical isolation state;
when the delivery pump is started, the liquid oxidant in the oxidant storage tank is pressurized and delivered 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, the delivery pump in the first sub-stage is a turbine pump, and the turbine pump is used for pressurizing an oxidant and then delivering the oxidant into the combustion chamber of the first sub-stage.
According to the carrier rocket of the solid-liquid hybrid power, the conveying pump in the second sub-stage is an electric pump, and the electric pump is used for pressurizing the oxidant and then conveying the oxidant into the combustion chamber of the second sub-stage.
According to the carrier rocket of the solid-liquid hybrid power provided by the invention, the liquid oxidant is nitric acid, liquid oxygen and N 2 O、H 2 O 2 At least one of the solidsThe fuel is at least one of polyethylene PE, hydroxyl-terminated polybutadiene HTPB, polymethyl methacrylate PMMA and paraffin wax.
According to the solid-liquid hybrid power carrier rocket provided by the invention, the upper stage is internally provided with the rail attitude control system, and the rail attitude control system comprises a plurality of rail attitude control engines capable of providing radial power, and is used for controlling the flight trajectory of the rocket in the flight process and sending the effective load into a preset orbit.
The invention provides a launch method of a carrier rocket of 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, starting the solid-liquid hybrid rocket engine of the boosting stage and the first sub-stage;
after flying for a first preset time period, the solid-liquid hybrid rocket engine of the boosting stage is shut down, and the boosting stage is separated;
after flying for a second preset time period, separating the second sub-stage from the first sub-stage by a preset distance;
after flying for a third preset time period, starting the solid-liquid hybrid rocket engine of the second sub-stage, and thermally separating the first sub-stage;
after the propulsion stage is finished, the solid-liquid hybrid rocket engine of the second sub-stage is shut down, and the second sub-stage is separated in a cold mode, so that the upper stage enters the gliding stage;
after correcting the glide track of the upper stage, igniting the liquid rocket engine of the upper stage to send the payload into a preset track 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 provided by the embodiment of the invention, the solid-liquid hybrid rocket engine is adopted as a main power system in the boosting stage, the first sub-stage and the second sub-stage, so that the advantages of high specific impulse, adjustable thrust, capability of being started in a plurality of times of shutdown and easiness in storage of the solid rocket engine, simple structure, high reliability and low maintenance cost are considered, the quick response capability is realized, and meanwhile, the cost is reduced, so that the commercial value and the economic benefit of the carrier rocket are ensured.
In the method for launching the solid-liquid hybrid power carrier rocket provided by the embodiment of the invention, the carrier rocket adopting the solid-liquid hybrid power has the advantages as described above, and the description is omitted here.
Additional aspects and advantages of embodiments of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of embodiments of the invention.
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 flow chart of a method for launching a solid-liquid hybrid launch vehicle according to the present invention.
Reference numerals:
10: a sub-stage; 11: a sub-level engine; 12: a sub-level oxidizer reservoir; 13: a sub-grade solid fuel tank;
20: a second sub-stage; 21: a secondary engine; 22: a secondary oxidant reservoir; 23: a secondary solid fuel tank; 24: a gesture control power system;
30: an upper stage; 31: a payload; 32: an instrument pod; 33: a rail gesture control system;
40: a fairing; 50: a boost stage; 60: a second-stage interstage section; 70: a tail cabin; 80: a secondary inter-stage section.
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.
In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In describing embodiments of the present invention, it should be noted that, unless explicitly stated and limited otherwise, the terms "coupled," "coupled," and "connected" should be construed broadly, and may be either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in embodiments of the present invention will be understood in detail by those of ordinary skill in the art.
In embodiments of the invention, unless expressly specified and limited otherwise, a first feature "up" or "down" on a second feature may be that the first and second features are in direct contact, or that the first and second features are in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
The examples provided by the present invention will now be described with reference to fig. 1 to 2, it being understood that the following are merely illustrative embodiments of the present invention and are not to be construed as limiting the present invention in any way.
The invention provides a carrier rocket with solid-liquid hybrid power, and fig. 1 is a schematic structural view of the carrier rocket with solid-liquid hybrid power, please refer to fig. 1. The carrier rocket of the solid-liquid hybrid power comprises: a first sub-stage 10, a second sub-stage 20, an upper stage 30, a fairing 40, and a plurality of boost stages 50. The carrier rocket refers to a carrier for pushing various spacecrafts to space. The parts are matched with each other, so that the launch work of the carrier rocket can be completed.
In this launch vehicle, the first sub-stage 10, the second sub-stage 20 and the upper stage 30 are detachably connected in this order. That is, the above-mentioned parts are connected during assembly, testing, transportation, and launching, and gradually separated during the flying process, so as to complete the launching work.
The boosting stages 50 are detachably connected to the side of one sub-stage 10, and the boosting stages 50 can be separated after the completion of the work, so as to reduce the weight of other continuous flight parts and facilitate the subsequent flight.
Further, a payload 31 is provided in the upper stage 30, wherein the payload 31 may be an artificial earth satellite, a manned spacecraft, a space station, an inter-satellite detector, or the like, and the payload 31 may be fed into a predetermined orbit by the carrier rocket.
The fairing 40 is covered outside the upper stage 30 to protect the internal devices and provide a barrier within the cover. In particular, the fairing 40 may be configured to avoid high temperatures and pressures experienced by the device due to the harsh environment encountered by the rocket during its traversing the atmosphere. Therefore, the fairing 40 is thrown away after the rocket has flown out of the atmosphere.
In the solid-liquid hybrid carrier rocket provided in this embodiment, the first sub-stage 10, the second sub-stage 20 and the booster stage 50 all adopt solid-liquid hybrid rocket engines as main power systems, and the solid-liquid hybrid rocket engines adopt liquid oxidants and solid fuels. 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 carrier rocket has longer working time, larger rocket model, stronger carrying capacity and high reliability, and can be used as a medium-large rocket.
Moreover, the upper stage 30 employs a liquid rocket engine. The liquid rocket engine has high fuel energy density and specific impulse, is easy to realize flow control and thrust adjustment, and can be shut down and started for multiple times.
Based on the engines, the carrier rocket is operated, the quick response capability can be achieved, and meanwhile, the cost is reduced, so that the commercial value and the economic benefit of the carrier rocket are guaranteed.
According to the carrier rocket adopting the solid-liquid hybrid power, provided by the embodiment of the invention, the solid-liquid hybrid rocket engine is adopted as a main power system in the boosting stage 50, the first sub-stage 10 and the second sub-stage 20, so that the advantages of high specific impulse, adjustable thrust, multiple shutdown starting, easiness in storage of the solid rocket engine, simple structure, high reliability and low maintenance cost of the solid rocket engine are considered, the cost can be reduced while the quick response capability is realized, and the commercial value and the economic benefit of the carrier rocket are ensured.
It should be noted that, the fairing 40 includes a cover body, an instrument cabin 32, a satellite and arrow separation mechanism, and the like, where the instrument cabin 32 is fixedly disposed in the cover body; the satellite separation mechanism is disposed on the instrument pod 32, and the instrument pod 32 is connected to the upper stage 30. Further, the solid-liquid hybrid launch vehicle may further include a tail cabin 70 disposed at the tail of the sub-stage 10.
In one embodiment provided by the invention, a liquid oxidizer employed in a solid-liquid hybrid rocket engine is physically isolated from a solid fuel prior to ignition. By placing the two in different spaces, contact is avoided before use, so as to ensure safety.
Further, in one embodiment provided by the present invention, a solid-liquid hybrid rocket engine includes a gasifier, an oxidizer reservoir, a transfer pump, and a solid fuel tank. The fuel gas generator can generate combustion gas with certain pressure and temperature, the oxidant storage tank is used for containing liquid oxidant, and the solid fuel tank is used for containing solid fuel. The gas generator and the transfer pump are both fixedly arranged between the oxidizer storage tank and the solid fuel tank. The liquid oxidizer in the oxidizer reservoir may be pressurized and delivered to the solid fuel tank by a delivery pump. The high-temperature fuel gas generated by the fuel gas generator is changed into high-speed air flow to be ejected through the spray pipe at the tail part so as to push the rocket to advance.
As can be seen in fig. 1, in a sub-stage 10, a sub-stage engine 11, a sub-stage oxidizer tank 12 and a sub-stage solid fuel tank 13 are provided; in the first sub-stage 10, a second sub-stage engine 21, a second sub-stage oxidizer tank 22, and a second sub-stage solid fuel tank 23 are provided.
In a further embodiment of the present invention, the solid-liquid hybrid rocket engine further comprises an engine thrust chamber and a nozzle, the engine thrust chamber being configured to control the nozzle using thrust vectoring. Specifically, the swing angle of the spray pipe is controlled through thrust vector so as to control the flight trajectory of the carrier rocket in the flight process. This configuration can greatly reduce the tank size of the attitude control power system 24 and the filling quality of the liquid propellant, thereby reducing the cost of the rocket.
In particular, the nozzle may be a flexible nozzle or a ball-and-socket nozzle. It will be appreciated that in the present invention, the nozzle described above can be used not only with solid-liquid hybrid rocket engines of the first sub-stage 10, the second sub-stage 20 and the booster stage 50, but also with liquid rocket engines of the upper stage 30. At any stage in the carrier rocket flight process, the swing angle of the spray section can be controlled by 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 carrier rocket of the invention can control the flying attitude in other modes, such as arranging a fluid secondary injection system at the nozzle of the rocket engine, so that the fluid of liquid or gas is injected into the jet flow of the engine through the nozzle diffusion section. The injected fluid creates a shock wave in the supersonic jet stream causing an imbalance in the pressure distribution, thereby deflecting the stream.
Still further, in one embodiment provided by the invention, when the delivery pump is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant storage tank and the solid fuel tank to form a physical isolation state, so that the safety is high, and the maintenance cost is reduced; when the delivery pump is started, the liquid oxidant in the oxidant storage tank is pressurized and delivered 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.
The conveying pump adopts electric energy as an energy source, and 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 by the conveying pump, so that the thrust of the carrier rocket can be regulated easily. Under the condition that the delivery pump is stopped, physical isolation is formed between the liquid oxidant and the solid fuel which are respectively stored in the oxidant storage tank and the solid fuel tank, so that the safety is high, and the starting and stopping of the solid-liquid hybrid rocket engine can be controlled at any time by controlling the delivery pump, so that the carrier rocket can adapt to more complex flight environments.
In one embodiment of the present invention, the transfer pump in a sub-stage 10 is a turbo pump, which is a power pump, the heart portion of the rocket engine. The turbo pump is used to boost the oxidant and deliver it to the combustion chamber of a sub-stage 10. The oxidant is pressurized by the turbine pump and enters the combustion chamber to be mixed with the pyrolysis gas of the solid fuel for combustion. Specifically, in one sub-stage 10, the engine diameter is 3m, the average thrust during operation is 2000kN, and the operating time is 190s.
In one embodiment of the present invention, the delivery pump in the secondary stage 20 is an electric pump that uses a high-energy battery and a motor-driven pump to boost the propellant, and the electric pump is used to boost the oxidant and deliver it to the combustion chamber of the secondary stage 20. The oxidant is pressurized by the electric pump and then delivered into the combustion chamber to be mixed with the pyrolysis gas of the solid fuel for combustion. The electric pump 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. Specifically, in the second sub-stage 20, the engine diameter is 3m, the vacuum average thrust is 400kN, and the operating time is 160s.
In one embodiment provided by the invention, the liquid oxidizer is nitric acid, liquid oxygen, N 2 O、H 2 O 2 The solid fuel is at least one of polyethylene PE, hydroxyl-terminated polybutadiene HTPB, polymethyl methacrylate PMMA and paraffin wax.
In one embodiment of the present invention, a rail attitude control system 33 is disposed in the upper stage 30, the rail attitude control system 33 including a plurality of rail attitude control engines capable of providing radial power for controlling the trajectory of the rocket during flight and delivering the payload 31 to a predetermined orbit.
In the upper stage 30, through the liquid rail attitude control system 33, not only is the main device rapidly launched, but also the carrying capacity of the rocket is further improved, and the solid-liquid hybrid engine can be designed into a CBC (Common Booster Core, public booster core) configuration, so that the carrying capacity can be greatly improved. Specifically, CBC configuration refers to a polished rod configuration that binds a number of sub-stages 10 as boosters. Wherein the binding of 2 primary stages 10 as boosters is of 3CBC configuration, such as delta 4 heavy, heavy falcon, new generation manned rocket; binding 4 sub-stages 10 as boosters is of 5CBC configuration, e.g. An Jiala A5.
The upper stage 30 power system adopts a liquid orbit attitude control rocket engine, and has wide thrust adjustment range and high attitude control precision. In the upper stage 30, the engine diameter was 2m, the vacuum average thrust was 83.3kN, and the operating time was 200s.
Further, the rail attitude control system 33 includes a helium bottle, a high pressure valve, a filter, a pressure reducing valve, an electromagnetic valve, and a rail attitude control thrust chamber; the helium bottle is connected with the filter through a high-pressure valve; the other end of the filter is provided with a pressure reducing valve; one end of the pressure reducing valve, which is far away from the filter, is provided with an electromagnetic valve; one end of the electromagnetic valve, which is far away from the pressure reducing valve, is provided with a rail gesture control thrust chamber.
It should be noted that the rail attitude control system 33 may also be disposed in the secondary-tertiary stage 60, which is not limited in this embodiment.
In addition, a attitude control power system 24 may be further disposed in the first sub-stage 10 and the second sub-stage 20, and in particular, an attitude control engine may be disposed in an inter-stage section between the first sub-stage 10 and the second sub-stage 20, and the attitude control engine may be started to provide power for adjusting the flight attitude of the carrier rocket in the radial direction of the carrier rocket by injecting air flow in the radial direction of the carrier rocket. In practical applications, the number of the attitude control engines is preferably multiple, and the multiple attitude control engines can be arranged on the first sub-stage 10, the second sub-stage 20 and the upper stage 30 of the carrier rocket or on any stage section among the first sub-stage 10, the second sub-stage 20 and the upper stage 30 according to the emission requirement. Preferably, the first sub-stage 10 and the second sub-stage 20 are respectively provided with four attitude control engines, and the upper stage 30 is provided with at least six attitude control engines so as to respectively cope with attitude control requirements of the carrier rocket when in lift-off and track-in.
It should be noted that the gesture control power system 24 may also be disposed in the secondary stage 80, which is not limited in this embodiment.
For example, in the present embodiment, the attitude control systems on the first sub-stage 10 and the second sub-stage 20 each use four thrusters as power; the rail attitude control system 33 on the upper stage 30 uses six thrusters as power.
The solid-liquid hybrid power carrier rocket provided by the embodiment of the invention can also be used for manufacturing an aircraft by adopting a light high-strength composite material, so that the weight of the rocket body structure is greatly reduced, and the rocket power required for launching the spacecraft is greatly reduced. The main technical performance table of the carrier rocket is shown in the following table 1:
TABLE 1 Main technical Performance Meter of Carrier rocket
According to the carrier rocket adopting the solid-liquid hybrid power, provided by the embodiment of the invention, the solid-liquid hybrid rocket engine is adopted as a main power system in the boosting stage 50, the first sub-stage 10 and the second sub-stage 20, so that the advantages of high specific impulse, adjustable thrust, multiple shutdown starting, easiness in storage of the solid rocket engine, simple structure, high reliability and low maintenance cost of the solid rocket engine are considered, the cost can be reduced while the quick response capability is realized, and the commercial value and the economic benefit of the carrier rocket are ensured.
Furthermore, in the solid-liquid hybrid rocket engine, when the delivery pump is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant storage tank and the solid fuel tank, so that a physical isolation state is formed, the safety is high, and the maintenance cost is reduced.
The invention provides a launch method of a solid-liquid hybrid launch vehicle, which is applied to any one of the above solid-liquid hybrid launch vehicles, and fig. 2 is a schematic flow chart of the launch method of the solid-liquid hybrid launch vehicle provided by the invention, please refer to fig. 2. The transmitting method comprises the following steps:
the carrier rocket can adopt a three-level launch testing mode of horizontal assembly, horizontal test and horizontal transportation, and after the carrier rocket is transported to a launch point by a motor vehicle and erected, the launch vehicle is evacuated, and the attitude is adjusted to launch.
101. After completion of the launch preparation, the solid-liquid hybrid rocket engine of the booster stage 50 and the one sub-stage 10 is started.
After launch of the vehicle, the booster stage 50 and the one-stage engine 11 reach altitude and speed via a vertical takeoff segment, a programmed turn phase, a zero angle of attack flight segment.
102. After flying for a first preset period of time, the solid-liquid hybrid rocket engine of the boosting stage 50 is shut down, and the boosting stage 50 is separated.
After the first preset time of flight, after the two boosting stages 50 are shut down, the separating rocket and the explosion bolt which are arranged at the rear part of the boosting stages 50 work to separate the boosting stages 50 from the sub-stage 10, namely, the boosting stages 50 are separated from the rocket main body, so that the rocket main body continues to fly. The first preset duration may be set according to needs, for example, the first preset duration may be 160s.
The rocket stage separation parts are generally connected by explosion bolts, and the explosion bolts are used for breaking the connecting pieces between the rocket stages, namely unlocking. After the connection is broken, there are two ways of interstage separation: and (5) heat separation and cold separation. Thermal separation refers to the pushing away of the subsequent stage of rocket by the high temperature gas flow emitted by the previous stage of rocket engine, so that the previous stage of rocket engine is ignited when the connecting piece is unlocked. The cold separation is to separate the front and rear two-stage rockets by the thrust of the thrust-back rocket on the rear one-stage rocket, and the engine of the front one-stage rocket needs to be ignited after the front and rear two-stage rockets are separated.
103. After flying for a second preset period of time, the second sub-stage 20 is separated from the first sub-stage 10 by a preset distance.
After continuing to fly for a second preset period of time, the explosion bolts arranged on the secondary stage section work, and the secondary stage is separated by a small distance under the action of aerodynamic resistance. The second preset duration may be set as required, for example, the second preset duration may be 5s. The preset distance may be set as needed, and this embodiment is not limited thereto.
104. After flying for a third preset period of time, the solid-liquid hybrid rocket engine of the second sub-stage 20 is started, and the first sub-stage 10 is thermally separated.
After the third preset time of continuous flight, the solid-liquid hybrid rocket engine of the second sub-stage 20 operates in an ignition mode, and the fuel gas flow generated by the spray pipe pushes the first sub-stage 10 away to realize thermal separation. The third preset duration may be set as required, for example, the third preset duration may be 2s.
105. After the propulsion phase is finished, the solid-liquid hybrid rocket engine of the second sub-stage 20 is shut down, and the second sub-stage 20 is separated cold, so that the upper stage 30 enters the gliding phase.
In the step, according to a preset scheme, the two-stage 20 rocket engine enters a program pitch angle flight state, and a ground control station monitors the flight process and corrects the course through a carrier rocket/ground data link.
After the work is finished, the solid-liquid hybrid rocket engine of the second sub-stage 20 is shut down, the explosion bolts of the second three-stage section 60 work, the cold separation between stages is realized, and the cold separation enters the gliding section.
106. After correcting the glide track of the upper stage 30, the liquid rocket engine of the upper stage 30 is ignited to send the payload 31 into a predetermined track in a three-axis stable posture.
The rail attitude control engine starts to work to adjust the orbit in the gliding process, the liquid rocket engine at the upper stage 30 is ignited after the completion, and meanwhile, the effective load 31 is sent into the preset orbit in a triaxial stable attitude under the correction of the rail attitude control engine.
107. Upon entering the predetermined track, the upper stage 30 releases the payload 31.
After entering the predetermined orbit, the payload 31 release mechanism in the upper stage 30 releases the payload 31, completing the overall operation of the launch vehicle.
According to the launch method of the solid-liquid hybrid power launch vehicle, provided by the embodiment of the invention, the solid-liquid hybrid rocket engine is adopted as a main power system in the boosting stage 50, the first sub-stage 10 and the second sub-stage 20, so that the advantages of high specific impulse, adjustable thrust, multiple shutdown starting, easiness in storage of the solid rocket engine, simple structure, high reliability and low maintenance cost of the solid rocket engine are considered, the cost can be reduced while the quick response capability is realized, and the commercial value and the economic benefit of the launch vehicle are ensured.
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 solid-liquid hybrid launch vehicle, comprising: a first sub-stage (10), a second sub-stage (20), an upper stage (30), a fairing (40) and a plurality of boost stages (50);
wherein the first sub-stage (10), the second sub-stage (20) and the upper stage (30) are connected in sequence in a separable way, a payload (31) is arranged in the upper stage (30), the fairing (40) covers the outside of the upper stage (30), and a plurality of boosting stages (50) are connected on the side face of the first sub-stage (10) in a separable way;
the first sub-stage (10), the second sub-stage (20) and the boosting stage (50) are all solid-liquid hybrid rocket engines, and liquid oxidants and solid fuels are adopted in the solid-liquid hybrid rocket engines;
the upper stage (30) adopts a liquid rocket engine;
the solid-liquid hybrid rocket engine comprises a spray pipe, wherein a fluid secondary injection system is arranged at the spray pipe, fluid of liquid or gas is injected into engine jet flow through a spray pipe diffusion section by the fluid secondary injection system, the injected fluid generates oblique shock waves in supersonic spray pipe airflow to cause unbalanced pressure distribution, so that the airflow is deflected, and the jet flow is used for controlling the flight attitude of the solid-liquid hybrid rocket engine.
2. A solid-liquid hybrid launch vehicle according to claim 1, wherein the liquid oxidizer employed in the solid-liquid hybrid rocket engine is physically isolated from the solid fuel prior to ignition.
3. A solid-liquid hybrid launch vehicle according to claim 2, wherein the solid-liquid hybrid rocket engine comprises a gas generator, an oxidizer reservoir, a transfer pump and a solid fuel tank;
the gas generator and the delivery pump are both fixedly disposed between the oxidizer storage tank and the solid fuel tank.
4. A solid-liquid hybrid launch vehicle according to claim 3, wherein the solid-liquid hybrid rocket engine further comprises an engine thrust chamber for controlling the nozzle using thrust vectors.
5. The solid-liquid hybrid vehicle according to claim 4, wherein,
when the delivery pump is not started, the liquid oxidant and the solid fuel are respectively stored in the oxidant storage tank and the solid fuel tank to form a physical isolation state;
when the delivery pump is started, the liquid oxidant in the oxidant storage tank is pressurized and delivered 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.
6. A solid-liquid hybrid launch vehicle according to claim 3, wherein the transfer pump in the first sub-stage (10) is a turbo pump for pressurizing the oxidant and transferring it into the combustion chamber of the first sub-stage (10).
7. A solid-liquid hybrid launch vehicle according to claim 3, wherein the transfer pump in the secondary stage (20) is an electric pump for pressurizing the oxidant and transferring it into the combustion chamber of the secondary stage (20).
8. A solid-liquid hybrid launch vehicle according to claim 1, wherein the liquid oxidizer is nitric acid, liquid oxygen, N 2 O、H 2 O 2 The solid fuel is at least one of polyethylene PE, hydroxyl-terminated polybutadiene HTPB, polymethyl methacrylate PMMA and paraffin wax.
9. A solid-liquid hybrid launch vehicle according to claim 1, characterized in that a rail attitude control system (33) is provided in the upper stage (30), said rail attitude control system (33) comprising a plurality of rail attitude control engines capable of providing radial power for controlling the trajectory of the rocket during flight and for feeding the payload (31) into a predetermined trajectory.
10. A method of launching a solid-liquid hybrid launch vehicle, characterized by being applied to the solid-liquid hybrid launch vehicle of any one of claims 1-9, the method comprising:
starting the solid-liquid hybrid rocket engine of the boosting stage (50) and the first sub-stage (10) after the completion of the launching preparation work;
after flying for a first preset time period, the solid-liquid hybrid rocket engine of the boosting stage (50) is shut down, and the boosting stage (50) is separated;
after flying for a second preset period of time, separating the second sub-stage (20) from the first sub-stage (10) by a preset distance;
after flying for a third preset time period, starting a solid-liquid hybrid rocket engine of the second sub-stage (20), and thermally separating the first sub-stage (10);
after the propulsion stage is finished, the solid-liquid hybrid rocket engine of the second sub-stage (20) is shut down, and the second sub-stage (20) is separated in a cold mode, so that the upper stage (30) enters the gliding stage;
after correcting the glide trajectory of the upper stage (30), the liquid rocket engine of the upper stage (30) is ignited to feed the payload (31) into a predetermined trajectory in a three-axis stable posture;
upon entering the predetermined track, the upper stage (30) releases the payload (31).
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| GB1134835A (en) * | 1965-12-06 | 1968-11-27 | Us Navy | Liquid injection thrust vectoring |
| WO2005049999A1 (en) * | 2003-11-18 | 2005-06-02 | Nederlandse Organisatie Voor Toegepast- Natuurwetenschappelijk Onderzoek Tno | Process for igniting a rocket engine and rocket engine |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
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| CN218329572U (en) * | 2022-11-16 | 2023-01-17 | 东方空间技术(山东)有限公司 | Solid-liquid mixed carrier rocket for continuously boosting in atmosphere |
| CN218495947U (en) * | 2022-10-26 | 2023-02-17 | 中国人民解放军63921部队 | Solid-liquid mixed carrier rocket |
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2023
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB1134835A (en) * | 1965-12-06 | 1968-11-27 | Us Navy | Liquid injection thrust vectoring |
| WO2005049999A1 (en) * | 2003-11-18 | 2005-06-02 | Nederlandse Organisatie Voor Toegepast- Natuurwetenschappelijk Onderzoek Tno | Process for igniting a rocket engine and rocket engine |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
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