CN109707538A - The sub- grade of the one of rocket and rocket - Google Patents
The sub- grade of the one of rocket and rocket Download PDFInfo
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- CN109707538A CN109707538A CN201910022750.1A CN201910022750A CN109707538A CN 109707538 A CN109707538 A CN 109707538A CN 201910022750 A CN201910022750 A CN 201910022750A CN 109707538 A CN109707538 A CN 109707538A
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Abstract
This application involves field of aerospace technology, a more particularly to a kind of sub- grade and rocket for rocket, it include: ontology, and sequentially connected oxidant stores component in the axial direction of the ontology, oxidant provisioning component and engine pack, the engine pack includes the first engine and the second engine, first engine and the ontology are coaxially disposed, second engine has at least two, each second engine is evenly arranged the ontology circumferentially around first engine, second engine with the oxidant provisioning component is separable links together.The application can largely avoid a sub- grade of current rocket larger technical problem of invalid load in removal process, improve the efficiency of rocket.
Description
Technical field
This application involves field of aerospace technology more particularly to the sub- grades and rocket of a kind of rocket.
Background technique
With the continuous development of aeronautical and space technology, oneself all moonlets of more and more colleges and universities and research institute are needed
It asks.The spacecrafts such as satellite need to carry carrier rocket injection, and still, traditional rocket is disposable type product, this leads
It causes the cost of transmitting high, most of R&D institution is made to hang back, hinder the fast development of mankind's solar-system operation, reduce hair
The expense of penetrating is always the expectation of people.Therefore, reusable rocket becomes the important directions of the following space flight development.
Reusable carrier rocket refers to take off from ground and complete predetermined launch mission after, completely or partially return and pacify
It is complete to land, by repair and maintenance and fuel adding, the rocket of launch mission can be executed again.The concept of recoverable launch vehicle
It is for Expendable launch vehicle.Currently, having been developed that on the market may be reused carrier rocket,
One grade be usually it is in parallel by multiple engines, when transmitting, works at the same time, and generating thrust by carrier rocket two, three sub- grades and has
It imitates load and is sent into predetermined altitude；When recycling, a sub- grade is started to work after reaching predetermined position and posture, and constantly regulate thrust,
Recoil effect is generated, realizes grease it in.
In recycling, usually all structures recycle the sub- grade of rocket one, but rocket engine is at work, temperature at present
Height causes combustion chamber and Nozzle ablation serious, and in many cases, the jet pipe of recycling and combustion chamber can not reuse, and needs
It replaces, therefore, in removal process, which wastes completely, forms larger invalid load, and cause recycling quality big,
Inertia is big, needs the thrust of engine bigger, and the working time is longer, and efficiency is very low, does not meet quick reusable small-sized fortune
Carry the original design intention of rocket.
Summary of the invention
This application provides the sub- grades and rocket of a kind of rocket, largely to avoid a sub- grade of current rocket
The larger technical problem of invalid load, improves the efficiency of rocket in removal process.
To achieve the goals above, the application uses following technical scheme:
The one aspect of the application provides an a kind of sub- grade of rocket, comprising: ontology, and in the axial direction of the ontology
Sequentially connected oxidant storage component, oxidant provisioning component and engine pack,
The engine pack includes the first engine and the second engine, and first engine and the ontology are coaxial
Setting, second engine have at least two, and each second engine is in the ontology circumferentially around described first
Engine is evenly arranged,
Second engine with the oxidant provisioning component is separable links together.
Preferably, each second engine is connect with the oxidant provisioning component by the first blasting bolt.
The beneficial effect of the technical solution is: this facilitates the other parts of a sub- grade of the second engine of control and rocket
Separation.The second high-pressure solenoid valve and the second engine can be connected by the first blasting bolt.
Preferably, the ontology includes separable the first receiving portion and the second receiving portion to link together, the hair
Motivation component is mounted in first receiving portion, and the oxidant storage component and the oxidant provisioning component are mounted on institute
It states in the second receiving portion.
The beneficial effect of the technical solution is: this facilitates the separation between the first receiving portion of control and the second receiving portion.
Specifically, the first receiving portion low layer covering can be made, make the high-rise covering of the second receiving portion, and use low layer covering with a thickness of
The aluminium alloy of 0.8mm makes, and high-rise covering uses to be made with a thickness of the aluminium alloy of 1mm.
Preferably, it is linked together between first receiving portion and second receiving portion by the second blasting bolt.
The beneficial effect of the technical solution is: this facilitates the separation between the first receiving portion of control and the second receiving portion.
After rocket flies out atmosphere, the second blasting bolt work, the connection between the first receiving portion and the second receiving portion is disconnected, and first
Receiving portion falls off from rocket main body.
Preferably, including landing chassis, the landing chassis include multiple struts, and the strut has and second receiving portion
Outer wall connection connecting pin, the connecting pin of each strut is uniformly distributed in the circumferential direction of second receiving portion.
The beneficial effect of the technical solution is: this makes a sub- grade of rocket provided by the embodiment of the present application in recycling
It is easier to land, avoids the damage when landing of a sub- grade of rocket as far as possible.
Preferably, the connecting pin and second receiving portion are hinged, so that the strut can turn to and described
The position of the outer wall fitting of two receiving portions.
The beneficial effect of the technical solution is: this landing chassis when not in use and can be close to the second receiving portion to set
It sets, as far as possible obstruction of the reduction landing chassis to the movement of a sub- grade of rocket and rocket.When the sub- grade of the one of rocket is close to ground,
Continental shelf is opened, and each strut is made to turn to the lower section of the second receiving portion, and when landing avoids the first engine and collision on the ground, and relies on
The recoil thrust settling landing of first engine completes recycling.
Preferably, first engine and the oxidant provisioning component are detachably connected.
The beneficial effect of the technical solution is: this facilitates a sub- grade of rocket after recycling to being likely to occur the of damage
The replacement of one engine, and then a sub- grade of rocket is enable to be used again.
Preferably, first engine includes combustion chamber and jet pipe, and the jet pipe removably connects with the combustion chamber
It connects.
The beneficial effect of the technical solution is: when combustion chamber or jet pipe damage, the component of damage can be replaced,
And unspoiled component can reuse, and improve the utilization rate of component, reduce costs.Combustion chamber and jet pipe preferably may be used
For the component that can individually produce in batches.
Preferably, including pipeline assembly, the pipeline assembly and the engine pack and the oxidant provisioning component
It is detachably connected.
The beneficial effect of the technical solution is: this convenient replacement to pipeline assembly, and then realizes a sub- grade of rocket
Reuse.
Further aspect of the application provides rocket, the sub- grade including above-mentioned rocket.
Technical solution provided by the present application can achieve it is following the utility model has the advantages that
The sub- grade of one of rocket provided by the embodiment of the present application can be realized a sub- grade of rocket with rocket motion to certain
When height, the second engine and rocket are separately from other sections, and then are avoided in the sub- grade recycling of rocket, the second engine
Invalid load is formed, inertia, the thrust of engine and operating time is reduced, and then improve the efficiency of rocket, makes rocket more
Meet the original design intention of quick reusable pencil rocket.
The additional technical feature and its advantage of the application will illustrate more obvious in following description content, or pass through
The concrete practice of the application is recognized that.
Detailed description of the invention
In order to illustrate more clearly of the technical solution of the application specific embodiment, specific embodiment will be described below
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is some implementations of the application
Mode for those of ordinary skill in the art without creative efforts, can also be according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the structural schematic diagram of a sub- grade of rocket provided by the embodiments of the present application；
Fig. 2 is the structural representation that each component in inside of a sub- grade of rocket provided by the embodiments of the present application passes through piping connection
Figure；
Fig. 3 is a kind of structural schematic diagram of the landing state of a sub- grade of rocket provided by the embodiments of the present application；
Fig. 4 is the structural schematic diagram of rocket provided by the embodiments of the present application.
Appended drawing reference:
The sub- grade of the one of 100- rocket；The first engine of 111-；The combustion chamber 111a-；111b- jet pipe；The second engine of 112-；
120- oxidant provisioning component；121- electric blasting valve；The second low-voltage solenoid valve of 122-；123- is adjustable Venturi tube；The Ni-based silver-colored net of 124-
Catalytic bed；130- oxidant stores component；131- oxidant storage box；132- high pressure gas cylinder；The first high-pressure solenoid valve of 141-；
The second high-pressure solenoid valve of 142-；143- inflates/releases hand valve；The first low-voltage solenoid valve of 144-；145- pressure gauge；146- is unidirectional
Valve；151- strut；The first receiving portion of 161-；The second receiving portion of 162-.
Specific embodiment
It is clearly and completely described below in conjunction with technical solution of the attached drawing to the application, it is clear that described implementation
Example is some embodiments of the present application, instead of all the embodiments.Based on the embodiment in the application, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall in the protection scope of this application.
In the description of the present application, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for describe the application and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present application, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in application.
As shown in Figs 1-4, the one aspect of the application provides an a kind of sub- grade of rocket, comprising: ontology, and in ontology
Axial direction on sequentially connected oxidant storage component 130, oxidant provisioning component 120 and engine pack,
Engine pack includes the first engine 111 and the second engine 112, and the first engine 111 is coaxially set with ontology
It sets, the second engine 112 has at least two, and each second engine 112 is in the uniform circumferentially around the first engine 111 of ontology
Arrangement,
Second engine 112 with oxidant provisioning component 120 is separable links together.
The sub- grade 100 of one of rocket provided by the embodiment of the present application can be realized a sub- grade 100 of rocket with rocket motion
When to certain altitude, the second engine 112 is separately from other sections with rocket, and then avoids recycling in a sub- grade 100 of rocket
When, the second engine 112 forms invalid load, reduces inertia, the thrust of engine and operating time, and then improve rocket
Efficiency, so that rocket is more met the original design intention of quick reusable pencil rocket.
Specifically, one of rocket provided by the embodiment of the present application sub- grade 100 is usually and in other sub- grades of rocket
One or more connection uses, and engine generally comprises jet pipe and combustion chamber, generates powered belt by engine and moves rocket motion；
The application the first engine 111 and the second engine 112 are preferably hybrid rocket engine.
The sub- grade 100 of one of rocket provided by the embodiment of the present application preferable use such as flowering structure: oxidant storage group
Part 130 includes high pressure gas cylinder 132 and oxidant storage box 131, by the between high pressure gas cylinder 132 and oxidant storage box 131
One low-voltage solenoid valve 144 connects, and the inflation on the high pressure gas cylinder 132/release hand valve 143 is pacified on oxidant storage box 131
Equipped with pressure gauge 145 and check valve 146；Oxidant provisioning component 120 includes sequentially connected electric blasting valve 121, the second low tension
Magnet valve 122, adjustable Venturi tube 123 and Ni-based silver-colored net catalytic bed 124, electric blasting valve 121 is connect with oxidant storage box 131, Ni-based
Silver-colored net catalytic bed 124 is connect by high-pressure solenoid valve with engine pack, corresponding first high-pressure solenoid valve of the first engine 111
141 and corresponding second high-pressure solenoid valve 142 of each second engine 112.
The sub- grade 100 of one of rocket provided by the embodiment of the present application preferably uses following application method: launch installation
When, the first low-voltage solenoid valve 144 is closed, and is inflated by inflating/releasing hand valve 143 to high pressure gas cylinder 132, is reached pressure requirements
When, hand valve 143 is inflated/is released in closing.Meanwhile liquid oxidizer fills in oxidant storage box 131 from check valve 146.Oxygen
131 both ends of agent storage box are elliposoidal, and centre is cylinder, are made of composite material, have liquid inside oxidant storage box 131
Capsule and anti-spigot.When 131 adding amount of oxidant storage box reaches requirement, stop filling, check valve 146 is closed.Transmitting prepares
In overall process, electric blasting valve 121 is in close state, the component after preventing oxidant from entering.
When starting transmitting, the second engine 112 starting, first the first low-voltage solenoid valve 144 is opened, and high pressure gas cylinder 132 is logical
It crosses pipeline to be pressurized to oxidant storage box 131, pressure gauge 145 monitors pressure in oxidant storage box 131, when meeting pressure requirements
When, electric blasting valve 121 is opened, and the second low-voltage solenoid valve 122 is opened, and liquid oxidizer flows into adjustable Venturi tube 123 by pipeline, can
Venturi tube 123 is adjusted by cavitation erosion Venturi tube and at its throat center one conical surface is installed with one heart and is formed.Pass through the control conical surface
Axial displacement, thus it is possible to vary the circulation area of oxidant in cavitation erosion Venturi tube to change oxidant mass flow, and then changes
Engine oxygen fires ratio, to realize change motor power.Oxidant enters Ni-based silver net catalysis after adjustable Venturi tube 123
Bed 124, Catalytic Decomposition of Hydrogen Peroxide generate high-temperature vapor and oxygen.After loine pressure reaches predetermined value, start with second
The second high-pressure solenoid valve 142 that machine 112 connects opens simultaneously, and high-temperature gas enters combustion chamber, after the spray of head, fills with solid
The abundant reactive combustion of medicine generates high temperature and high pressure gas by spraying after nozzle expansion and generates huge thrust.
When rocket reaches predetermined altitude, the sub- work of grade 100 of the one of rocket terminates, and the first low-voltage solenoid valve 144 is closed, and is stopped
Oxidant storage box 131 is pressurized, after pressure reduction to specified value, closes the second low-voltage solenoid valve 122, stop liquid oxidant
Supply, the second engine 112 are all closed, and the second engine 112 is separated with rocket main body.After separation 1 second, the sub- grade of the one of rocket
100 separate with rocket rest part.
After the sub- grade 100 of the one of rocket separates, beginning is unpowered to be slided, and posture engine carries out pose adjustment, reaches predetermined
After height and Gesture, the first low-voltage solenoid valve 144 is opened, and high pressure gas cylinder 132 is increased by pipeline to oxidant storage box 131
Pressure, pressure gauge 145 monitors pressure in oxidant storage box 131, and when meeting pressure requirements, the second low-voltage solenoid valve 122 is opened,
Liquid oxidizer flows into adjustable Venturi tube 123 by pipeline, and after catalytic decomposition, the first high-pressure solenoid valve 141 is opened, oxidant into
The combustion chamber for entering the first engine 111 sprays after being mixed and burned with fuel from jet pipe, generates recoil thrust, realizes to rocket
The continuous reduction of speed of one sub- grade 100.During recovery flight, adjustable Venturi tube 123 is constantly regulate, the first engine 111 of control pushes away
The one of rocket 100 speed of grade when reaching ground, is reduced to 0, completes recycling by power.Three sons of the sub- grade 200 of the two of rocket and rocket
The work in succession of grade 300, completes the transport task for payload 500, and radome fairing 400 is located at the top of rocket, protects and effectively carries
Lotus.
Preferably, each second engine 112 is connect with oxidant provisioning component 120 by the first blasting bolt.This is convenient
Control the separation of the second engine 112 and the other parts of a sub- grade 100 of rocket.Second can be connected by the first blasting bolt
High-pressure solenoid valve 142 and the second engine 112.
Preferably, ontology includes separable the first receiving portion 161 and the second receiving portion 162 to link together, is started
Thermomechanical components are mounted in the first receiving portion 161, and oxidant storage component 130 and oxidant provisioning component 120 are mounted on the second appearance
It receives in portion 162.This facilitates the separation between the first receiving portion 161 of control and the second receiving portion 162.Specifically, the first appearance can be made
Portion 161 is received as low layer covering, makes the high-rise covering of the second receiving portion 162, and use low layer covering and close with a thickness of the aluminium of 0.8mm
Gold production, high-rise covering uses to be made with a thickness of the aluminium alloy of 1mm.
Preferably, it is linked together between the first receiving portion 161 and the second receiving portion 162 by the second blasting bolt.This
Facilitate the separation between the first receiving portion 161 of control and the second receiving portion 162.After rocket flies out atmosphere, the second explosion spiral shell
Bolt work, the connection between the first receiving portion 161 and the second receiving portion 162 disconnect, and the first receiving portion 161 takes off from rocket main body
It falls.
Preferably, one of rocket provided by the embodiment of the present application sub- grade 100 includes landing chassis, and landing chassis includes multiple
Bar 151, strut 151 have the connecting pin connecting with the outer wall of the second receiving portion 162, and the connecting pin of each strut 151 holds second
Receive portion 162 circumferential direction on be uniformly distributed.This is easier to a sub- grade 100 of rocket provided by the embodiment of the present application in recycling
Land avoids the damage when landing of a sub- grade 100 of rocket as far as possible.
Preferably, connecting pin and the second receiving portion 162 are hinged, so that strut 151 can turn to and the second receiving portion 162
Outer wall fitting position.This, which makes landing chassis when not in use, can be close to the setting of the second receiving portion 162, reduce as far as possible
Obstruction of the continental shelf to the movement of a sub- grade 100 of rocket and rocket.When the sub- grade 100 of the one of rocket is close to ground, landing chassis is opened,
Each strut 151 is set to turn to the lower section of the second receiving portion 162, when landing avoids the first engine 111 and collision on the ground, and relies on
The recoil thrust settling landing of first engine 111 completes recycling.
Preferably, the first engine 111 and oxidant provisioning component 120 are detachably connected.This facilitates a son of rocket
100 replacement after recycling to the first engine 111 for being likely to occur damage of grade, so enable a sub- grade 100 of rocket by
It reuses.
Preferably, the first engine 111 includes combustion chamber 111a and jet pipe 111b, and jet pipe 111b and combustion chamber 111a are removable
It connects with unloading.When combustion chamber 111a or jet pipe 111b is damaged, the component of damage can be replaced, and unspoiled component can
To reuse, the utilization rate of component is improved, is reduced costs.Combustion chamber 111a and jet pipe 111b may preferably be and can distinguish
The component individually produced in batches.
Preferably, one of rocket provided by the embodiment of the present application sub- grade 100 include pipeline assembly, pipeline assembly with start
Thermomechanical components and oxidant provisioning component 120 are detachably connected.This convenient replacement to pipeline assembly, and then realize the one of rocket
Sub- grade 100 reuses.
Further aspect of the application provides rocket, the sub- grade including rocket provided by above-mentioned the embodiment of the present application
100。
Rocket provided by the embodiment of the present application passes through the sub- grade 100 to rocket provided by the embodiment of the present application
Use, when can be realized a sub- grade 100 of rocket with rocket motion to certain altitude, the second engine 112 and rocket other
It is partially separated, and then avoids in a sub- grade 100 recycling of rocket, the second engine 112 forms invalid load, reduces used
Property, the thrust of engine and operating time, and then improve the efficiency of rocket, meet rocket more quickly reusable small-sized
The original design intention of rocket.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the application, rather than its limitations；To the greatest extent
Pipe is described in detail the application referring to foregoing embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, each embodiment technology of the application that it does not separate the essence of the corresponding technical solution
The range of scheme.
In addition, it will be appreciated by those of skill in the art that although above-mentioned some embodiments include institute in other embodiments
Including certain features rather than other feature, but the combination of the feature of different embodiment means in scope of the present application
Within and form different embodiments.For example, in claims above, embodiment claimed it is any it
One can in any combination mode come using.In addition, the information disclosed in the background technology section is intended only to deepen pair
The understanding of the general background technology of the application, and be not construed as recognizing or implying in any form that information composition has been this
The prior art well known to the technical staff of field.
Claims (10)
1. the sub- grade of the one of rocket characterized by comprising ontology, and the sequentially connected oxidation in the axial direction of the ontology
Component, oxidant provisioning component and engine pack are stored in agent,
The engine pack includes the first engine and the second engine, and first engine is coaxially set with the ontology
It sets, second engine has at least two, and each second engine is in the ontology circumferentially around first hair
Motivation is evenly arranged,
Second engine with the oxidant provisioning component is separable links together.
2. the sub- grade of the one of rocket according to claim 1, which is characterized in that each second engine and the oxidant
Provisioning component is connected by the first blasting bolt.
3. the sub- grade of the one of rocket according to claim 1, which is characterized in that the ontology includes separable being connected to one
The first receiving portion and the second receiving portion risen, the engine pack are mounted in first receiving portion, the oxidant storage
Hiding component and the oxidant provisioning component are mounted in second receiving portion.
4. the sub- grade of the one of rocket according to claim 3, which is characterized in that first receiving portion and described second accommodates
It is linked together between portion by the second blasting bolt.
5. the sub- grade of the one of rocket according to claim 3, which is characterized in that including landing chassis, the landing chassis includes more
A strut, the strut have the connecting pin connecting with the outer wall of second receiving portion, and the connecting pin of each strut is in institute
It states and is uniformly distributed in the circumferential direction of the second receiving portion.
6. the sub- grade of the one of rocket according to claim 5, which is characterized in that the connecting pin and second receiving portion are cut with scissors
It connects, so that the strut can turn to the position being bonded with the outer wall of second receiving portion.
7. the sub- grade of the one of rocket according to claim 1, which is characterized in that first engine and the oxidant supply
Answer component detachably connected.
8. the sub- grade of the one of rocket according to claim 1, which is characterized in that first engine includes combustion chamber and spray
Pipe, the jet pipe and the combustion chamber are detachably connected.
9. one of rocket described in any one of -8 sub- grade according to claim 1, which is characterized in that including pipeline assembly, institute
It states pipeline assembly and the engine pack and the oxidant provisioning component is detachably connected.
10. rocket, which is characterized in that the sub- grade including the rocket as described in any one of claim 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910022750.1A CN109707538B (en) | 2019-01-10 | 2019-01-10 | Rocket and one-stage thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910022750.1A CN109707538B (en) | 2019-01-10 | 2019-01-10 | Rocket and one-stage thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109707538A true CN109707538A (en) | 2019-05-03 |
| CN109707538B CN109707538B (en) | 2020-11-24 |
Family
ID=66259930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910022750.1A Active CN109707538B (en) | 2019-01-10 | 2019-01-10 | Rocket and one-stage thereof |
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| Country | Link |
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| CN (1) | CN109707538B (en) |
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| CN110775301A (en) * | 2019-12-04 | 2020-02-11 | 哈尔滨工业大学 | Aircraft with high rail-entering efficiency and strong maneuvering capability and rail-entering method thereof |
| CN112722334A (en) * | 2021-02-18 | 2021-04-30 | 星河动力(北京)空间科技有限公司 | Carrier rocket and rocket sublevel recovery control method |
| CN113202631A (en) * | 2021-04-26 | 2021-08-03 | 于力 | Oxygen supplementing device for turbine shaft and turboprop engine and working method of oxygen supplementing device |
| CN113608452A (en) * | 2021-10-09 | 2021-11-05 | 星河动力(北京)空间科技有限公司 | Semi-physical simulation platform for reusing carrier rocket navigation system |
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| CN109163624A (en) * | 2018-09-27 | 2019-01-08 | 宁波天擎航天科技有限公司 | A kind of separable rocket propulsion system |
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| CN108869097A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | A kind of posture control system and Small Launch Vehicle |
| CN108895921A (en) * | 2018-07-03 | 2018-11-27 | 北京航空航天大学 | Hydrogen peroxide attitude control system for solid-liquid hybrid power carrier rocket |
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| CN110775301A (en) * | 2019-12-04 | 2020-02-11 | 哈尔滨工业大学 | Aircraft with high rail-entering efficiency and strong maneuvering capability and rail-entering method thereof |
| CN112722334A (en) * | 2021-02-18 | 2021-04-30 | 星河动力(北京)空间科技有限公司 | Carrier rocket and rocket sublevel recovery control method |
| CN112722334B (en) * | 2021-02-18 | 2022-05-17 | 星河动力(北京)空间科技有限公司 | Carrier rocket and rocket sublevel recovery control method |
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| CN113608452A (en) * | 2021-10-09 | 2021-11-05 | 星河动力(北京)空间科技有限公司 | Semi-physical simulation platform for reusing carrier rocket navigation system |
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| Publication number | Publication date |
|---|---|
| CN109707538B (en) | 2020-11-24 |
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