CN106837610B - A kind of close-coupled works long hours solid-liquid rocket catalysis bed structure - Google Patents
A kind of close-coupled works long hours solid-liquid rocket catalysis bed structure Download PDFInfo
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- CN106837610B CN106837610B CN201710217293.2A CN201710217293A CN106837610B CN 106837610 B CN106837610 B CN 106837610B CN 201710217293 A CN201710217293 A CN 201710217293A CN 106837610 B CN106837610 B CN 106837610B
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- catalytic bed
- engine
- skull
- support frame
- oxidant
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Classifications
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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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The present invention discloses a kind of close-coupled and works long hours solid-liquid rocket catalysis bed structure, belongs to solid-liquid rocket field, including oxidizer catalytic bed component, engine skull, burning chamber shell and catalytic bed support frame.Oxidizer catalytic bed component is the integrated tubular structure being made of oxidant liquid spray panel, catalytic bed annular outer cover and oxidant gas spray panel, internal loading catalyst.Oxidizer catalytic bed component is fixed on the inside of engine skull by catalytic bed support frame, to reduce engine overall volume.It is bonded high temperature resistant heat insulation layer respectively on the inside of catalytic bed support frame wall surface and engine skull, to carry out thermal protection in engine works long hours to it.Catalytic bed support frame can form one section of changeover portion after catalytic bed component, conduct heat to avoid high-temperature fuel gas in combustion chamber to the flowing of catalytic bed component and excessively.
Description
Technical field
The present invention relates to solid-liquid rocket catalytic ignition technical fields, are a kind of close-coupled long-times specifically
The solid-liquid rocket that works is catalyzed bed structure, is suitable for solid-liquid more sensitive to structure size, and having repeatedly starting demand
Rocket engine.
Background technique
Solid-liquid rocket is that a kind of new rocket combined using liquid oxidizer and solid fuel as propellant is pushed away
Into system.Because of its unique physical structure, solid-liquid rocket is able to have both some traditional solid propellant rockets and liquid fire
The characteristics of arrow engine, have cost is relatively low, safety is good, and the feature of environmental protection is good, and structure is simple, and propellant energy is relatively high, Yi Shixian
The advantages that thrust adjusts and repeatedly starts.In aerospace field, the middle-size and small-size sounding rocket especially in civil aerospace technology field is dynamic
The development prospect of Force system, inferior orbital vehicle dynamical system and middle-size and small-size Satellite attitude and orbit control dynamical system etc. is generally had an optimistic view of.
Due to using the propellant combination of different, the non-premixs of object phase, solid-liquid rocket is difficult to realize Self-lighting,
Therefore, it has become one of the key technologies in solid-liquid rocket application for firing technique.In solid-liquid rocket, usually
Using igniter type ignition schemes or oxidizer catalytic formula ignition schemes.The usual structure of igniter type ignition schemes is more simple
It is single, but can only realize the single igniting of solid-liquid rocket.And in oxidizer catalytic ignition schemes, catalytic bed can be passed through
Promote oxidizer catalytic decomposition, decomposing the heat solid fuel powder column released using oxidant makes its pyrolysis to realize
The igniting of solid-liquid rocket.Oxidizer catalytic ignition schemes can effectively realize the multiple igniting of solid-liquid rocket,
Especially suitable for there is the solid-liquid rocket of repeatedly starting demand.
However, catalytic bed usually requires additionally to occupy biggish space in engine front, so as to cause solid-liquid rocket hair
Motivation entirety contour dimension obviously increases.And requirement of the rocket-powered flight device often for component structural size is very severe
It carves, the increase of dynamical system overall dimensions can significantly affect the overall performance of rocket-powered flight device.Therefore, it is necessary to be multiple
Starting solid-liquid rocket designs a kind of compact-sized, and the oxidizer catalytic bed that will not additionally increase engine contour dimension is set
Catalytic bed is built in front of engine and fires indoor organization plan and can achieve above-mentioned purpose by meter scheme.But due to solid-liquid fire
It is exceedingly odious that indoor thermal environment is fired before arrow engine, for the solid-liquid rocket to work long hours, built-in catalysis
Bed thermal protection conceptual design is more difficult.
Summary of the invention
To solve the above-mentioned problems, a kind of close-coupled is proposed in the present invention to work long hours solid-liquid rocket catalysis
Bed structure.Oxidizer catalytic bed is installed on before solid-liquid rocket and fires chamber interior, therefore will not additionally increase engine
Whole contour dimension.Meanwhile passing through reasonable catalytic bed mounting structure and thermal protection conceptual design, it is ensured that catalytic bed is in heat
Combustion interior is reliable and stable before the exceedingly odious engine of environment works long hours.
Close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure, including oxidizer catalytic bed component,
Engine skull, burning chamber shell and catalytic bed support frame.
The oxidizer catalytic bed component is tubular structure, internal loading catalyst；Oxidizer catalytic bed component top surface with
Bottom surface is respectively oxidant liquid spray panel and oxidant gas spray panel.Oxidizer catalytic bed component is arranged in catalytic bed
In support frame, catalytic bed support frame connects bolt by support frame and is installed on the inside of engine skull, realizes oxidizer catalytic bed group
Coaxial fixation between part and engine skull；On catalytic bed support frame, at catalyst bed component rear, design has one section of oxidation
Gas changeover portion is decomposed in agent.Fastening is attached using combustion chamber connection bolt between the burning chamber shell and engine skull.
The design of above-mentioned engine skull center has oxidant inlet, and in engine skull and oxidant liquid spray panel
Between have oxidant liquid collecting head cavity；On the wall surface of above-mentioned catalytic bed support frame, on the inside of engine skull and combustor outer casing
Support frame heat insulation layer, skull heat insulation layer made of high-temperature resistant thermal insulating material and combustion chamber heat insulation layer are bonded on inner wall respectively.
In the solid-liquid rocket course of work, liquid oxidizer by oxidant inlet on skull flow into skull with
In oxidant liquid collecting head cavity between oxidant liquid spray face, it is oxidized after agent is full of in liquid collecting head cavity, oxidant is conveying
Under the pressure effect of system, by oxidant liquid spray panel even into catalytic bed.In catalytic bed, liquid oxidizer
Catalytic decomposition is the higher oxidant gas of temperature under the catalytic action of catalyst, and oxidant gas passes through oxidant gas later
The uniform spray of body spray panel enters in engine combustion room.In engine combustion room, oxidant gas is to solid fuel medicine
Column carries out inertia heating, its pyrolysis is made to generate fuel gas.Finally, oxidant gas burns after blending with fuel gas,
To realize the igniting of solid-liquid rocket.
The present invention has the advantages that
1, close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure, will be consolidated using catalytic bed support frame
The catalytic bed of liquid rocket engine fires chamber interior before being installed on solid-liquid rocket, is realizing the same of oxidizer catalytic decomposition
When, it will not additionally increase the contour dimension of solid-liquid rocket, can effectively control the overall volume of engine, more adapt to
The demand of Power System of Flight Vehicle.
2, close-coupled of the present invention works long hours solid-liquid rocket catalysis bed structure, using catalytic bed support frame and its
Inside and outside heat insulation layer exports one section of changeover portion of formation between preceding combustion room in catalytic bed, can use before the section effectively obstructs engine
Flowing and heat transfer of the indoor high-temperature fuel gas to catalytic bed are fired, good thermal protection is formed to catalytic bed；
3, close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure, in catalytic bed support frame outside
And motor head covers bonding high-temperature resistant thermal insulating material, can form good heat to catalytic bed mounting structure and engine skull
Protection supports catalytic bed in particular with the ladder fit structure of structure between heat insulation layer outside skull heat insulation layer and support frame
Frame connection bolt also forms good thermal protection, it is ensured that catalytic bed and its mounting structure work long hours in engine
It does not fail；
4, during close-coupled of the present invention works long hours solid-liquid rocket catalysis bed structure, oxidizer catalytic bed component can
With the reuse of part as a whole, experimentation cost can be substantially reduced in ground experiment.
Detailed description of the invention
Fig. 1 be close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure cross-sectional view；
Fig. 2 be close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure in oxidizer catalytic bed component
Structural schematic diagram.
In figure:
1- oxidizer catalytic bed component 2- engine skull 3- burning chamber shell
4- catalytic bed support frame 5- support frame connects bolt 6- support frame heat insulation layer
The combustion chamber 7- skull heat insulation layer 8- heat insulation layer 9- solid fuel powder column
The combustion chamber 10- connects bolt 11- head cavity sealing ring 12- combustion chamber sealing circle
13- changeover portion 101- catalytic bed shell 102- oxidant liquid spray panel
103- oxidant gas spray panel 104- catalyst 201- oxidant inlet
202- oxidant liquid collecting head cavity
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
Close-coupled of the present invention work long hours solid-liquid rocket catalysis bed structure, including oxidizer catalytic bed component 1,
Engine skull 2, burning chamber shell 3 and catalytic bed support frame 4, as shown in Figure 1.
The oxidizer catalytic bed component 1 can repeatedly use in different solid rocket engine, including catalytic bed
Shell 101, oxidant liquid spray panel 102 and oxidant gas spray panel 103, as shown in Figure 2.Wherein, outside catalytic bed
Shell 101 is annular, and upper and lower two sides are respectively and outside oxidant liquid spray panel 102 and 103 side wall of oxidant gas spray panel
Edge is circumferentially welded as a whole, and to 101 inside loading catalyst 104 of catalytic bed shell.Above-mentioned oxidant liquid spray panel 102
Oxidant liquid spray orifice and oxidant gas spray orifice are respectively designed with on oxidant gas spray panel 103；Oxidant
Divide multi-tier arrangement on liquid injection hole and oxidant gas spray orifice circumferential direction, every layer of circumferential direction is uniformly distributed.
Above-mentioned oxidizer catalytic bed component 1 is installed on engine skull 2 by catalytic bed support frame 4.Wherein, catalytic bed
Support frame 4 is tubular structure, and part is separately designed with lower part as large diameter Duan Yu little internal diameter section thereon, and formed between the two it is fixed
Position shoulder.Catalyst bed component 1 is coaxially disposed in large diameter section, is positioned by locating shoulder, and catalyst bed
1 top surface of component is flushed with 4 top surface of catalytic bed support frame.There is support frame connection method in 4 top end circumferential direction of catalytic bed support frame
Orchid connects bolt 5 by support frame and catalytic bed support frame 4 is coaxially fixed on engine skull 2 across support frame connecting flange
Inside, and the positioning in 1 axial direction of oxidizer catalytic bed component is realized by 2 inner sidewall of engine skull and locating shoulder jointly.
Support frame heat insulation layer 6 made of high-temperature resistant thermal insulating material is bonded on 4 wall surface of catalytic bed support frame；Support frame heat insulation layer 6 covers
4 outside wall surface of catalytic bed support frame and small internal diameter section wall surface, while covering the circumferential upper circle of 4 lower end of catalytic bed support frame.
Above-mentioned 2 center of engine skull design has oxidant inlet 201, and sprays in engine skull 1 and oxidant liquid
Infusing has oxidant liquid collecting head cavity 202 between panel 102, urge to guarantee that oxidant can enter oxidant by uniform spray
Change in bed component 1；Head cavity sealing ring is installed between engine skull 2 and catalytic bed support frame 4 simultaneously, guarantees oxidant liquid collecting
The sealing performance of head cavity 202.2 inside of engine skull is also bonded with skull heat insulation layer 7, skull made of high-temperature resistant thermal insulating material
Heat insulation layer 7 covers catalytic bed support frame 4 on 2 inner wall of engine skull and blocks outer rest part；It can be right by skull heat insulation layer 7
Engine skull 2 forms good thermal protection effect, guarantees that engine skull 2 does not fail after engine works long hours.Institute
The Position Design that skull heat insulation layer 7 is stated close to catalytic bed support frame 4 is hierarchic structure, passes through hierarchic structure and catalytic bed support frame
Support frame connection 5 end of bolt covering is realized the heat-insulated of support frame connection bolt 5, prevented by the overlap joint cooperation of 4 top connecting flanges
Indoor high-temperature fuel gas is only fired before solid-liquid rocket quickly to be passed by the higher metal bolts of thermal conductivity to engine skull 2
Heat, and overheat engine skull 2.
It is attached fastening using combustion chamber connection bolt 10 between the engine skull 2 and burning chamber shell 3, and is made
Engine chamber is sealed with combustion chamber sealing circle.3 inner wall of burning chamber shell is bonded with to be prevented by high temperature resistant anti-ablation heat
Combustion chamber heat insulation layer 8 made of protective material, to protect burning chamber shell 3 will not be because of mistake during engine works long hours
Heat and fail.
In the igniting start-up course of solid-liquid rocket, liquid oxidizer passes through the oxidant on engine skull 2
Entrance 201 enters in oxidant liquid collecting head cavity 202.It is defeated in engine after oxidant liquid collecting head cavity 202 is full of by liquid oxidizer
The uniform spray of oxidant liquid spray orifice under the action of system upstream pressure by oxidant liquid spray panel 102 is sent to enter
In catalytic bed.In catalytic bed, catalytic decomposition is the higher oxygen of temperature to liquid oxidizer rapidly under the catalytic action of catalyst
Oxidant gas, oxidant gas enters by the oxidant gas spray orifice spray on oxidant gas spray panel 103 later
In engine combustion room.Oxidant gas carries out inertia heating after entering engine chamber, to solid fuel powder column 9, makes
It is generated fuel gas by thermal decomposition, is burnt after oxidant gas and fuel gas blending later, to realize solid-liquid fire
The igniting of arrow engine starts.
In solid-liquid rocket during working long hours, support frame heat insulation layer 6 carries out heat to catalytic bed support frame 4
Protection, skull heat insulation layer 7 connect bolt 5 with support frame to engine skull 2 and carry out thermal protection, 8 pairs of combustion chamber heat insulation layer burnings
Room housing 3 carries out thermal protection, it is ensured that above-mentioned structural member works long hours under the severe thermal environment of engine not to fail.Separately
Outside, catalytic bed support frame 4 and the outer heat insulation layer 10 of support frame, support frame internal insulation 11 utilize its ring structure in oxidant gas
Reduced diameter section is devised after spray panel 12, decomposes gas changeover portion 13 as an oxidant；It, can be in changeover portion 13
Flowing of the indoor high-temperature fuel gas to engine catalytic bed component is fired before effectively obstructing engine using the flowing of oxidant gas
And heat transfer, to guarantee that catalytic bed component will not fail after working long hours because temperature is excessively high.
Claims (3)
1. a kind of close-coupled works long hours, solid-liquid rocket is catalyzed bed structure, it is characterised in that: including oxidizer catalytic
Bed component, engine skull, burning chamber shell and catalytic bed support frame；
The oxidizer catalytic bed component is tubular structure, internal loading catalyst；Oxidizer catalytic bed component top surface and bottom surface
Respectively oxidant liquid spray panel and oxidant gas spray panel；Oxidizer catalytic bed component is installed on solid-liquid rocket hair
Chamber interior is fired before motivation；
Above-mentioned oxidizer catalytic bed component is arranged in catalytic bed support frame, and catalytic bed support frame, which connects bolt by support frame, pacifies
On the inside of engine skull, oxidizer catalytic bed component and the coaxial fixation between engine skull are realized；In engine skull
Heart design has oxidant inlet, and has oxidant liquid collecting head cavity between engine skull and oxidant liquid spray panel；
Fastening is attached using combustion chamber connection bolt between the burning chamber shell and engine skull；
Skull heat insulation layer made of high-temperature resistant thermal insulating material is also bonded on the inside of engine skull, skull heat insulation layer covers engine
Catalytic bed support frame blocks outer rest part on skull inner wall；And skull heat insulation layer is close to the Position Design of catalytic bed support frame
For hierarchic structure, cooperated by hierarchic structure and catalytic bed top of support frame connecting flange overlap joint；
Above-mentioned catalytic bed support frame is tubular structure, and upper part and lower part separately design as large diameter Duan Yu little internal diameter section, and
Locating shoulder is formed between the two；Catalyst bed component is coaxially disposed in large diameter section, is positioned by locating shoulder；In small
Diameter section decomposes gas changeover portion as one section of oxidant below catalyst bed component；In changeover portion, oxidant is utilized
Flowing and heat transfer of the indoor high-temperature fuel gas to engine catalytic bed component are fired before the flowing of gas effectively barrier engine, is guaranteed
Catalytic bed component will not fail after working long hours because temperature is excessively high.
The solid-liquid rocket catalysis bed structure 2. a kind of close-coupled as described in claim 1 works long hours, it is characterised in that:
Oxidant decompose gas transition section length and catalytic bed support frame it is small it is interior through the ratio between section internal diameter be 0.2~0.5.
The solid-liquid rocket catalysis bed structure 3. a kind of close-coupled as described in claim 1 works long hours, it is characterised in that:
Head cavity sealing ring is installed between engine skull and catalytic bed support frame；Burning is installed between engine skull and burning chamber shell
Room sealing ring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710217293.2A CN106837610B (en) | 2017-04-05 | 2017-04-05 | A kind of close-coupled works long hours solid-liquid rocket catalysis bed structure |
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| CN201710217293.2A CN106837610B (en) | 2017-04-05 | 2017-04-05 | A kind of close-coupled works long hours solid-liquid rocket catalysis bed structure |
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| CN106837610B true CN106837610B (en) | 2019-08-06 |
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| CN107218857A (en) * | 2017-08-03 | 2017-09-29 | 北京航空航天大学 | Micro missile |
| CN112677499B (en) * | 2020-12-22 | 2022-12-27 | 上海航天化工应用研究所 | Solid rocket engine heat insulation layer roll extrusion paster device |
| CN114017208B (en) * | 2021-12-09 | 2023-05-09 | 北京航空航天大学 | Solid-liquid rocket engine catalytic bed and cooling and preheating system and method thereof |
| CN115523058B (en) * | 2022-09-30 | 2024-07-26 | 北京航空航天大学 | Buckle type solid-liquid rocket engine catalytic bed heat insulation structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102658066A (en) * | 2012-04-26 | 2012-09-12 | 葛明龙 | Catalytic decomposition low-concentration hydrogen peroxide reactor, combustion chamber and application thereof |
| 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 |
| CN105804889A (en) * | 2016-02-04 | 2016-07-27 | 北京航空航天大学 | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2367197A1 (en) * | 2001-01-10 | 2002-07-10 | Cesaroni Technology Incorporated | Liquid/solid fuel hybrid propellant system for a rocket |
| US7966805B2 (en) * | 2007-05-15 | 2011-06-28 | Raytheon Company | Hydroxyl amine based staged combustion hybrid rocket motor |
-
2017
- 2017-04-05 CN CN201710217293.2A patent/CN106837610B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102658066A (en) * | 2012-04-26 | 2012-09-12 | 葛明龙 | Catalytic decomposition low-concentration hydrogen peroxide reactor, combustion chamber and application thereof |
| 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 |
| CN105804889A (en) * | 2016-02-04 | 2016-07-27 | 北京航空航天大学 | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
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