CN107461277A - A kind of ground experiment modularization hybrid rocket engine - Google Patents
A kind of ground experiment modularization hybrid rocket engine Download PDFInfo
- Publication number
- CN107461277A CN107461277A CN201710941108.4A CN201710941108A CN107461277A CN 107461277 A CN107461277 A CN 107461277A CN 201710941108 A CN201710941108 A CN 201710941108A CN 107461277 A CN107461277 A CN 107461277A
- Authority
- CN
- China
- Prior art keywords
- module
- spray
- rocket engine
- chamber
- hybrid rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a kind of ground experiment modularization hybrid rocket engine, it is related to Aero-Space technical field of engines.The ground experiment modularization hybrid rocket engine includes oxidant liquid collecting module, ignition module, combustor module, rear head module and the jet pipe module being sequentially communicated；The oxidant liquid collecting module, ignition module, combustor module, rear head module detachably connect successively with jet pipe module.The ground experiment modularization hybrid rocket engine of the present invention, using dismountable modularized design, include oxidant liquid collecting module, ignition module, combustor module, rear head module and jet pipe module, and take the mechanical seal interface of unified standard, different tests need to only carry out the change in design of a small amount of module, improve comparative between engine test data, simplify the design of experiment hybrid rocket engine, reduce ground experiment cost.
Description
Technical field
The present invention relates to Aero-Space technical field of engines, more particularly to a kind of ground experiment to be mixed with modularization solid-liquid
Rocket engine.
Background technology
Hybrid rocket engine refer to incendiary agent be solid and oxidant be liquid engine.Said from performance,
The specific impulse of hybrid rocket engine is higher than solid propellant rocket, less than energized fluid engine, with the liquid that can be stored
Engine is suitable, has the advantages of simple and compact for structure.
Existing experiment hybrid rocket engine, lacks unified code requirement, and durability is poor, cause experiment into
This is higher.Also, it is unfavorable for the data comparison of different tests, is unfavorable for the research of test value car following-theory, pair of Numerical Simulation Results
Than.
The content of the invention
It is existing to solve it is an object of the invention to provide a kind of ground experiment modularization hybrid rocket engine
Durability existing for ground experiment hybrid rocket engine in technology is poor, experimentation cost is high, is unfavorable for test data
The problems such as contrast.
To achieve these goals, the present invention uses following technical scheme：
A kind of ground experiment modularization hybrid rocket engine provided by the invention, including the oxidation being sequentially communicated
Agent liquid collecting module, ignition module, combustor module, rear head module and jet pipe module；The oxidant liquid collecting module, the point
Fiery module, the combustor module, the rear head module detachably connect successively with the jet pipe module.
Further, the oxidant liquid collecting module, the ignition module, the combustor module, the rear head module
It is close by the annular boss, annular groove and annular of mutual cooperation between the jet pipe module at least two adjacent modules
Seal sealing connection.The technical scheme has technical effect that：When oxidant liquid collecting module connects with ignition module sealing, oxygen
The connecting end surface of agent liquid collecting module sets annular boss, and the connecting end surface of ignition module sets annular groove, and annular is recessed
O-ring seal is placed inside groove.Annular boss cooperation is caught in the annular groove and abuts O-ring seal so that oxidant
The connecting end surface of liquid collecting module and the connecting end surface of ignition module are fitted and connected, and form oxidant liquid collecting module internal cavity, igniting mould
Structure of the inner chamber of block with exterior space sealing isolation.
Further, the ignition module includes spray chamber and fire chamber, the oxidant liquid collecting module, the spray
Chamber, the fire chamber and the combustor module are sequentially communicated.The technical scheme has technical effect that：Carry out autoxidator
The oxidant of liquid collecting module realizes spray and atomization in spray chamber, and igniting startup is carried out subsequently into fire chamber.Likewise,
Oxidant liquid collecting module, spray chamber, fire chamber and combustor module are sequentially communicated, and at least two adjacent modules it
Between positioning carried out by annular boss, annular groove and O-ring seal connected with sealing.
Further, the spray chamber includes spray housing and spray panel；It is provided with the spray panel multiple flat
Straight direct-injection through hole, the spray panel are built in the spray housing；One side end face of the spray housing and the oxidation
Agent liquid collecting module sealing is connected, and the other end is tightly connected with the fire chamber, makes oxidant from the oxidant liquid collecting module
Enter the fire chamber after being atomized via the direct-injection through hole spray.The technical scheme has technical effect that：Spray housing
It is tightly connected for realizing, and sets direct-injection through hole to be used for the direct current atomization and spray for realizing oxidant on spray panel.
Further, the spray chamber includes spray housing, swirl atomizer housing and swirl atomizer blanking cover；The centrifugation spray
Mouth housing connects to form the centrifugal chamber for being built in the spray housing with the swirl atomizer blanking cover；The side of the centrifugal chamber
Wall is provided with multiple centrifugation through holes being vortexed relative to centrifugal chamber's axis；One side end face of the spray housing with it is described
Oxidant liquid collecting module sealing is connected, and the other end is tightly connected with the fire chamber, makes oxidant from the oxidant liquid collecting
Module enters the fire chamber after being atomized via the centrifugation through hole spray.The technical scheme has technical effect that：Spray
Housing, which is used to realize, to be tightly connected, and forms centrifugal chamber after swirl atomizer housing and the installation of swirl atomizer blanking cover, passes through centrifugation
Through hole realizes centrifugal atomizing and the spray of oxidant.
Alternatively, the ignition module includes catalytic bed chamber, the oxidant liquid collecting module, the catalytic bed chamber and
Combustor module is sequentially communicated.The technical scheme has technical effect that：Catalyst built in catalytic bed chamber, for liquid oxidation
The catalysis of agent, it is generally used for the catalysis of liquid oxidizer hydrogen peroxide or nitrous oxide.Catalytic effect is equally lighted a fire, and will can be aoxidized
High-temperature gas spray to combustor module is produced after agent catalysis and participates in combustion reaction.
Further, in addition to secondary injection module；The secondary injection module is arranged at the combustor module and described
Between rear head module.The technical scheme has technical effect that：Secondary injection module is in combustor module and rear head module
Between oxidant spray is atomized, strengthen the blending of oxidant and solid fuel, improve efficiency of combustion.
Further, in addition to before combustion room module, after-burning room module；Combustion room module is arranged at the combustor module before described
Front end；The after-burning room module is arranged at the rear end of the combustor module.The technical scheme has technical effect that：Preceding combustion
Room module and after-burning room module are respectively arranged at the front and back end of combustor module, are built-in with heat insulation layer so that shape among combustion chamber
Into high temperature recirculation zone, the combustion stability of strengthen burning room, efficiency of combustion is improved.In addition, the usual arrange parameter of after-burning room module
Measurement assembly, to detect internal pressure of combustion chamber, temperature variations.
Further, in addition to flow-disturbing module；The flow-disturbing module be arranged at the front end of the combustor module, rear end or
Stage casing.The technical scheme has technical effect that：Flow-disturbing module sets flow-disturbing hole, may be arranged at powder column front end, medicine in combustion chamber
Any position of among post or powder column rear end, equally plays the blending for promoting oxidant and fuel, improves the effect of efficiency of combustion
Fruit.
Further, in addition to measurement module；The measurement module is arranged at the combustor module and the rear head mould
Optional position between block.The technical scheme has technical effect that：Measurement module is according to being actually needed, with combustor module one
And or individually internal pressure of combustion chamber, temperature variations are detected.
The beneficial effects of the invention are as follows：
Ground experiment modularization hybrid rocket engine, using dismountable modularized design, includes oxidant
Liquid collecting module, ignition module, combustor module, rear head module and jet pipe module, and take the mechanical seal of unified standard to connect
Mouthful, different tests need to only carry out the change in design of a small amount of module, improve comparative between engine test data, simplify examination
The design with hybrid rocket engine is tested, reduces ground experiment cost.
Brief description of the drawings
In order to illustrate more clearly of the technical scheme of the specific embodiment of the invention, embodiment will be described below
In the required accompanying drawing used be briefly described.It should be evident that drawings in the following description are some implementations of the present invention
Mode, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is first type of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Fig. 2 is second of type of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Fig. 3 is the direct injection spray of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of chamber；
Fig. 4 is the centrifugal spray of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of chamber；
Fig. 5 is the fire chamber of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Fig. 6 is the catalytic bed chamber of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Fig. 7 is the secondary spray mould of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of block；
Fig. 8 is the preceding combustion room module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Fig. 9 is the after-burning room module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Figure 10 is the flow-disturbing module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart；
Figure 11 is the measurement module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart.
Reference：
1- oxidant liquid collecting modules；2- ignition modules；3- combustor modules；
4- rear head modules；5- jet pipe modules；A- annular boss；
B- annular grooves；21- spray chambers；22- fire chambers；
211- spray housings；212- spray panels；M- direct-injection through holes；
213- swirl atomizer housings；214- swirl atomizer blanking covers；N- centrifuges through hole；
23- catalytic bed chambers；Bis- injection modules of 6-；Room module is fired before 7-；
8- after-burning room modules；9- flow-disturbing modules；10- measurement modules.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than instruction or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that instruction or hint relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, with concrete condition above-mentioned term can be understood at this
Concrete meaning in invention.
DESCRIPTION OF THE PRIOR ART：
In the prior art, hybrid rocket engine refers to that incendiary agent is solid and oxidant is starting for liquid
Machine.To be said from performance, the specific impulse of hybrid rocket engine is higher than solid propellant rocket, less than energized fluid engine,
It is suitable with the liquid engine that can be stored, there is the advantages of simple and compact for structure.Existing experiment is started with hybrid rocket
Machine, lack unified code requirement, durability is poor, causes experimentation cost higher.Also, it is unfavorable for the data pair of different tests
Than being unfavorable for the research of test value car following-theory, the contrast of Numerical Simulation Results.
The specific embodiment of the invention：
A kind of ground experiment modularization hybrid rocket engine is present embodiments provided, wherein：Fig. 1 is the present invention
The structure chart for the ground experiment type of modularization hybrid rocket engine first that embodiment provides；Fig. 2 is the present invention
The structure chart of ground experiment second of type of modularization hybrid rocket engine that embodiment provides.As shown in Figure 1, 2,
Ground experiment modularization hybrid rocket engine include be sequentially communicated oxidant liquid collecting module 1, ignition module 2, combustion
Burn room module 3, rear head module 4 and jet pipe module 5.Wherein, oxidant liquid collecting module 1, ignition module 2, combustor module 3,
Rear head module 4 detachably connects successively with jet pipe module 5.
Ground experiment provided by the invention modularization hybrid rocket engine, can preferably solve prior art
Durability existing for middle ground experiment hybrid rocket engine is poor, experimentation cost is high, is unfavorable for test data contrast etc.
Problem：Oxidant liquid collecting module 1, ignition module 2, combustor module 3, rear head module 4 and jet pipe module 5 are designed as removable
The multiple modules unloaded, different tests need to only carry out the change in design of a small amount of module, improve the contrast between engine test data
Property, the design of experiment hybrid rocket engine is simplified, reduces ground experiment cost.During experiment, oxidant
Ignition module 2 is transported to from oxidant liquid collecting module 1, forms after high temperature and high pressure gas spray to combustor module 3 and solid combustion
Material blending burning, then the high temperature and high pressure gas after burning are oriented to jet pipe module 5 by rear head module 4 and sprayed backward, generation pushes away
Power.
On the basis of above-described embodiment, further, oxidant liquid collecting module 1, ignition module 2, combustor module 3,
It is recessed by the annular boss A of mutual cooperation, annular between rear head module 4 and at least two adjacent modules of jet pipe module 5
Groove B connects with O-ring seal (not marking) sealing.Specifically, connected as oxidant liquid collecting module 1 seals with ignition module 2
When, the connecting end surface of oxidant liquid collecting module 1 is provided with annular boss A, and the connecting end surface of ignition module 2 sets annular groove
B, and O-ring seal is placed inside annular groove B.Annular boss A cooperations are caught in annular groove B and abut ring packing
Circle so that the connecting end surface of the connecting end surface and ignition module 2 of oxidant liquid collecting module 1 is fitted and connected, and forms oxidant liquid collecting
The structure of the inner chamber of module 1, the inner chamber of ignition module 2 with exterior space sealing isolation.
Fig. 3 is the direct injection spray of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of chamber 21；Fig. 4 be ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention from
The structure chart of core type spray chamber 21；Fig. 5 sends out for ground experiment modularization hybrid rocket provided in an embodiment of the present invention
The structure chart of the fire chamber 22 of motivation.As seen in figures 3-5, on the basis of above-described embodiment, further, ignition module 2
Including spray chamber 21 and fire chamber 22, and oxidant liquid collecting module 1, spray chamber 21, fire chamber 22 and combustion chamber mould
Block 3 is sequentially communicated.Now, the oxidant for carrying out autoxidator liquid collecting module 1 realizes spray and atomization, Ran Houjin in spray chamber 21
Enter fire chamber 22 and carry out igniting startup.Likewise, oxidant liquid collecting module 1, spray chamber 21, fire chamber 22 and combustion chamber
Module 3 is sequentially communicated, and is entered between at least two adjacent modules by annular boss A, annular groove B and O-ring seal
Row positioning connects with sealing.
As shown in figure 3, on the basis of above-described embodiment, further, spray chamber 21 also includes the He of spray housing 211
Spray panel 212.Specifically, multiple straight direct-injection through hole M are provided with spray panel 212, and spray panel 212 is built in
In spray housing 211.Wherein, a side end face of spray housing 211 is tightly connected with oxidant liquid collecting module 1, the other end and point
Fiery chamber 22 is tightly connected, and oxidant is entered the igniting after being atomized from oxidant liquid collecting module 1 via direct-injection through hole M sprays
Chamber 22.In the structure design, spray housing 211, which is used to realize, to be tightly connected, and direct-injection through hole is set on spray panel 212
M is used for the direct current atomization and spray for realizing oxidant.
As shown in figure 4, on the basis of above-described embodiment, alternatively, spray chamber 21 also include spray housing 211, from
Heart nozzle body 213 and swirl atomizer blanking cover 214.Specifically, swirl atomizer housing 213 and swirl atomizer blanking cover 214 connect shape
Into the centrifugal chamber for being built in spray housing 211, and centrifugal chamber side wall be provided with it is multiple relative to centrifugal chamber's axis whirlpool
The centrifugation through hole N of rotation.Wherein, a side end face of spray housing 211 is tightly connected with oxidant liquid collecting module 1, the other end and point
Fiery chamber 22 is tightly connected, and makes oxidant from oxidant liquid collecting module 1 via inlet point fire chamber after centrifugation through hole N sprays atomization
22.In the structure design, spray housing 211, which is used to realize, to be tightly connected, and swirl atomizer housing 213 and swirl atomizer blanking cover
Centrifugal chamber is formed after 214 installations, centrifugal atomizing and the spray of oxidant are realized by centrifuging through hole N.
Fig. 6 is the catalytic bed chamber of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
23 structure chart.As shown in fig. 6, on the basis of above-described embodiment, alternatively, ignition module 2 includes catalytic bed chamber 23.Its
In, oxidant liquid collecting module 1, catalytic bed chamber 23 and combustor module 3 are sequentially communicated.In the structure design, catalytic bed chamber
Catalyst built in room 23, for the catalysis of liquid oxidizer, it is generally used for urging for liquid oxidizer hydrogen peroxide or nitrous oxide
Change.Catalytic effect is equally lighted a fire, and high-temperature gas spray to combustor module 3 can will be produced after oxidizer catalytic and participates in burning instead
Should.
Fig. 7 is the secondary spray mould of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of block 6.As shown in fig. 7, on the basis of above-described embodiment, further, secondary injection module 6 is additionally provided with, its
In, secondary injection module 6 is arranged between combustor module 3 and rear head module 4.Secondary injection module 6 is in combustor module 3
Oxidant spray is atomized between rear head module 4, strengthens the blending of oxidant and solid fuel, improves efficiency of combustion.
Fig. 8 is the preceding combustion room module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
7 structure chart；Fig. 9 is the afterburner mould of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
The structure chart of block 8.As shown in Figure 8,9, on the basis of above-described embodiment, further, combustion room module 7 is with after before being additionally provided with
Fire room module 8.Wherein, preceding combustion room module 7 is arranged at the front end of combustor module 3, and after-burning room module 8 is arranged at combustor module
3 rear end.In the structure design, preceding combustion room module 7 and after-burning room module 8 are respectively arranged at the front and back end of combustor module 3,
It is built-in with heat insulation layer so that high temperature recirculation zone is formed among combustion chamber, the combustion stability of strengthen burning room, improves burning effect
Rate.In addition, the usual arrange parameter measurement assembly of after-burning room module 8, to detect internal pressure of combustion chamber, temperature variations.
Figure 10 is the flow-disturbing module 9 of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
Structure chart.As shown in Figure 10, on the basis of above-described embodiment, further, it is additionally provided with flow-disturbing module 9.Wherein, flow-disturbing
Module 9 is arranged at the front end, rear end or stage casing of combustor module 3.In the structure design, flow-disturbing module 9 sets flow-disturbing hole,
May be arranged at powder column front end in combustion chamber, any position of among powder column or powder column rear end, equally play promote oxidant with
The blending of fuel, improve the effect of efficiency of combustion.
Figure 11 is the measurement module of ground experiment modularization hybrid rocket engine provided in an embodiment of the present invention
10 structure chart.As shown in figure 11, on the basis of above-described embodiment, further, it is additionally provided with measurement module 10.Wherein,
Measurement module 10 is arranged at the optional position between combustor module 3 and rear head module 4.In the structure design, mould is measured
Block 10 is examined to internal pressure of combustion chamber, temperature variations in the lump or individually according to being actually needed, with combustor module 3
Survey.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, either which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
1. a kind of ground experiment modularization hybrid rocket engine, it is characterised in that including the oxidant being sequentially communicated
Liquid collecting module, ignition module, combustor module, rear head module and jet pipe module；
The oxidant liquid collecting module, the ignition module, the combustor module, the rear head module and the jet pipe mould
Block detachably connects successively.
2. ground experiment according to claim 1 modularization hybrid rocket engine, it is characterised in that the oxygen
Agent liquid collecting module, the ignition module, the combustor module, the rear head module and the jet pipe module at least two
Connected between individual adjacent module by annular boss, the annular groove of mutual cooperation with O-ring seal sealing.
3. ground experiment according to claim 2 modularization hybrid rocket engine, it is characterised in that the point
Fiery module includes spray chamber and fire chamber, the oxidant liquid collecting module, the spray chamber, the fire chamber and institute
Combustor module is stated to be sequentially communicated.
4. ground experiment according to claim 3 modularization hybrid rocket engine, it is characterised in that the spray
Note chamber includes spray housing and spray panel；Multiple straight direct-injection through holes, the spray are provided with the spray panel
Panel is built in the spray housing；One side end face of the spray housing is connected with the oxidant liquid collecting module sealing, separately
One end is tightly connected with the fire chamber, makes oxidant from the oxidant liquid collecting module via the direct-injection through hole spray mist
Enter the fire chamber after change.
5. ground experiment according to claim 3 modularization hybrid rocket engine, it is characterised in that the spray
Note chamber includes spray housing, swirl atomizer housing and swirl atomizer blanking cover；The swirl atomizer housing and the swirl atomizer
Blanking cover connects the centrifugal chamber to be formed and be built in the spray housing；The side wall of the centrifugal chamber is provided with multiple relative to institute
State the centrifugation through hole that centrifugal chamber's axis is vortexed；One side end face of the spray housing connects with the oxidant liquid collecting module sealing
Connect, the other end is tightly connected with the fire chamber, makes oxidant from the oxidant liquid collecting module via the centrifugation through hole
Enter the fire chamber after spray atomization.
6. ground experiment according to claim 2 modularization hybrid rocket engine, it is characterised in that the point
Fiery module includes catalytic bed chamber, and the oxidant liquid collecting module, the catalytic bed chamber and combustor module are sequentially communicated.
7. the ground experiment modularization hybrid rocket engine according to any one of claim 1~6, its feature exist
In, in addition to secondary injection module；The secondary injection module be arranged at the combustor module and the rear head module it
Between.
8. the ground experiment modularization hybrid rocket engine according to any one of claim 1~6, its feature exist
In, in addition to preceding combustion room module, after-burning room module；Combustion room module is arranged at the front end of the combustor module before described；It is described
After-burning room module is arranged at the rear end of the combustor module.
9. the ground experiment modularization hybrid rocket engine according to any one of claim 1~6, its feature exist
In, in addition to flow-disturbing module；The flow-disturbing module is arranged at the front end, rear end or stage casing of the combustor module.
10. the ground experiment modularization hybrid rocket engine according to any one of claim 1~6, its feature
It is, in addition to measurement module；The measurement module is arranged at appointing between the combustor module and the rear head module
Meaning position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941108.4A CN107461277A (en) | 2017-10-11 | 2017-10-11 | A kind of ground experiment modularization hybrid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941108.4A CN107461277A (en) | 2017-10-11 | 2017-10-11 | A kind of ground experiment modularization hybrid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107461277A true CN107461277A (en) | 2017-12-12 |
Family
ID=60554175
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710941108.4A Pending CN107461277A (en) | 2017-10-11 | 2017-10-11 | A kind of ground experiment modularization hybrid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107461277A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590885A (en) * | 2018-05-10 | 2018-09-28 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
| CN110103378A (en) * | 2019-04-15 | 2019-08-09 | 中国科学院力学研究所 | A kind of the nested type powder column formation system and method for solid-liquid rocket |
| CN110700967A (en) * | 2019-09-03 | 2020-01-17 | 陕西蓝箭航天技术有限公司 | Liquid starter device and attitude control power system |
| CN111256543A (en) * | 2020-01-16 | 2020-06-09 | 西北工业大学 | Small solid-liquid sounding rocket for teaching science popularization |
| TWI720399B (en) * | 2019-01-04 | 2021-03-01 | 台灣晉陞太空股份有限公司 | Rocket engine with improved solid fuel column |
| CN115653788A (en) * | 2022-12-27 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen peroxide kerosene dual-component gas generator and working method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| CN106837609A (en) * | 2017-04-07 | 2017-06-13 | 北京航空航天大学 | A kind of change propulsive solid-liquid rocket two-way centrifugal injector structure |
| CN106870204A (en) * | 2017-01-19 | 2017-06-20 | 北京航空航天大学 | Disturbing flow device in the middle of solid-liquid rocket engine combustor |
-
2017
- 2017-10-11 CN CN201710941108.4A patent/CN107461277A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| CN106870204A (en) * | 2017-01-19 | 2017-06-20 | 北京航空航天大学 | Disturbing flow device in the middle of solid-liquid rocket engine combustor |
| CN106837609A (en) * | 2017-04-07 | 2017-06-13 | 北京航空航天大学 | A kind of change propulsive solid-liquid rocket two-way centrifugal injector structure |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590885A (en) * | 2018-05-10 | 2018-09-28 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
| CN108590885B (en) * | 2018-05-10 | 2019-05-10 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
| CN109441666B (en) * | 2018-10-30 | 2021-04-20 | 北京航空航天大学 | Tail vortex centrifugal injection type solid-liquid hybrid rocket engine |
| TWI720399B (en) * | 2019-01-04 | 2021-03-01 | 台灣晉陞太空股份有限公司 | Rocket engine with improved solid fuel column |
| CN110103378A (en) * | 2019-04-15 | 2019-08-09 | 中国科学院力学研究所 | A kind of the nested type powder column formation system and method for solid-liquid rocket |
| CN110700967A (en) * | 2019-09-03 | 2020-01-17 | 陕西蓝箭航天技术有限公司 | Liquid starter device and attitude control power system |
| CN111256543A (en) * | 2020-01-16 | 2020-06-09 | 西北工业大学 | Small solid-liquid sounding rocket for teaching science popularization |
| CN115653788A (en) * | 2022-12-27 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen peroxide kerosene dual-component gas generator and working method thereof |
| CN115653788B (en) * | 2022-12-27 | 2023-04-07 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen peroxide kerosene dual-component gas generator and working method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107461277A (en) | A kind of ground experiment modularization hybrid rocket engine | |
| CN109098892B (en) | A kind of engine combined power system based on alternative fuel | |
| CN103244968B (en) | There is the combustor assembly in standing vortex chamber | |
| CN102943719B (en) | Turbulence device for postcombustion chamber of hybrid rocket engine | |
| CN102175041B (en) | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter | |
| CN106134417B (en) | Low-thrust rocket | |
| CN203570457U (en) | Two-stage mixing type nozzle device | |
| CN203604065U (en) | Medium-concentration hydrogen peroxide/kerosene combustion chamber free of catalyst bed | |
| CN106555707A (en) | Electricity drives propellant-feed system liquid-propellant rocket engine | |
| CN108894893A (en) | Rocket punching press combined engine Film cooling Rocket ejector motor power room | |
| CN107956601A (en) | One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate | |
| JP2012500926A (en) | Combustion turbine for non-continuous combustion | |
| CN111828175B (en) | Pre-combustion heating device and rotary detonation engine using same | |
| CN103697471A (en) | Annular combustion chamber fuel gas generator using alcohol as fuel | |
| EP3341656A1 (en) | Systems and methods for a multi-fuel premixing nozzle with integral liquid injectors/evaporators | |
| CN218064968U (en) | Combustion nozzle and internal and external mixed combustion engine | |
| WO2014152320A4 (en) | Power-producing apparatus and method | |
| CN107676195B (en) | A kind of modularization rocket engine propellant biasing spray panel of cover board connection | |
| CN106870205B (en) | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber | |
| CN108953002A (en) | With the rocket series thrust chamber on single flow head and cooling discharge partition | |
| CN105715409A (en) | Annular solid-liquid catalytic ignition engine | |
| CN115075983A (en) | Gas generator and liquid rocket engine | |
| CN109723554B (en) | Central distribution plasma cracking activation oil supplementing device and method | |
| CN104154566A (en) | Dual-fuel nozzle structure of gas turbine | |
| CN103512047A (en) | Radial rotational flow double fuel nozzle for chemical regenerative cycle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171212 |