CN107143433A - Single group member liquid-propellant rocket engine radial direction chuck catalyst bed - Google Patents
Single group member liquid-propellant rocket engine radial direction chuck catalyst bed Download PDFInfo
- Publication number
- CN107143433A CN107143433A CN201710348921.0A CN201710348921A CN107143433A CN 107143433 A CN107143433 A CN 107143433A CN 201710348921 A CN201710348921 A CN 201710348921A CN 107143433 A CN107143433 A CN 107143433A
- Authority
- CN
- China
- Prior art keywords
- catalyst
- group member
- single group
- rocket engine
- catalyst bed
- 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.)
- Granted
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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/68—Decomposition chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Catalysts (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a kind of single group member liquid-propellant rocket engine radial direction chuck catalyst bed, it is by radial integrated formula injection device, demarcation strip, baffle plate, upper cover plate, lower cover is linked in sequence successively forms and is formed inner ring and outer ring, inner ring is designed with n independent decomposition chambers with outer ring, common 2n decomposition chamber, n is the natural number more than 2, each independent decomposition chamber of inner ring can add spontaneous catalyst, each independent decomposition chamber in outer ring can add spontaneous catalyst or non-spontaneous property catalyst, inner ring is typically equal with the quantity of outer ring plenum chamber, keep simultaneously consistent with the injection into orbit pipe quantity of radial integrated formula injection device.The present invention solves the catalyst bed configurations size increase that single group member liquid-propellant rocket engine is brought as thrust magnitude increases, catalyst bed bed load increase, engine life is reduced, the problems such as engine use reliability decline, achieve the beneficial effects such as single group member liquid-propellant rocket engine high thrust or change propulsive steady operation.
Description
Technical field
The present invention relates to a kind of catalyst bed, in particular it relates to which a kind of single group member liquid-propellant rocket engine radial direction chuck is urged
Agent bed.
Background technology
It, for carrying catalyst, is the significant components of single group member liquid-propellant rocket engine, its effect that catalyst bed, which is,
It is, by the gas working medium that propellant catalytic decomposition is high temperature, to realize chemical energy to hot transformation of energy.Influence catalyst bed design
Principal element has：Catalyst bed void fraction, catalyst bed specific surface area, catalyst bed bed and are urged at load, catalyst bed flow resistance
Agent activity itself etc..The single group member liquid-propellant rocket engine of routine application at present, the application of wherein catalyst has tended to be ripe,
In the larger-size catalyst bed design of catalyst bed configurations, catalysis is determined by catalyst natures such as catalyst shape, density
Agent bed voidage and specific surface area change are smaller.Catalyst bed bed load is the important parameter of catalyst bed design, its selection
Directly affect engine operational life, startability etc..In the design of high-thrust single constituent element catalytic bed, flowed using conventional axial
Bed structure is catalyzed, to ensure certain catalytic bed bed load, catalytic bed diameter is excessive, and larger choose is brought to product structure design
War, is unfavorable for realizing miniaturization and loss of weight.
The content of the invention
For defect of the prior art, radially pressed from both sides it is an object of the invention to provide a kind of single group member liquid-propellant rocket engine
Catalyst bed is covered, it solves the catalyst bed configurations size increasing that single group member liquid-propellant rocket engine is brought as thrust magnitude increases
Greatly, catalyst bed bed load increase, engine life is reduced, the problem such as engine use reliability decline, achieves single group member
The beneficial effect such as liquid-propellant rocket engine high thrust or change propulsive steady operation.
According to an aspect of the present invention there is provided a kind of single group member liquid-propellant rocket engine radial direction chuck catalyst bed, its
Be characterised by, the single group member liquid-propellant rocket engine radial direction chuck catalyst bed by radial integrated formula injection device, demarcation strip,
Baffle plate, upper cover plate, lower cover are linked in sequence successively forms and is formed inner ring and outer ring, and inner ring is designed with n independently with outer ring
Decomposition chamber, common 2n decomposition chamber, n is the natural number more than 2, and each independent decomposition chamber of inner ring can add spontaneous catalyst, outer ring
Each independent decomposition chamber can add spontaneous catalyst or non-spontaneous property catalyst, the general phase of quantity of inner ring and outer ring plenum chamber
Deng while keeping consistent with the injection into orbit pipe quantity of radial integrated formula injection device.
Preferably, the spontaneous catalyst or non-spontaneous property catalyst are independently divided by radially uniform spray into each
Solve room.
Preferably, the radial integrated formula injection device is sprayed after propellant, forms certain initial velocity under the effect of the pressure
Degree, jet direction is cylindrical radial, and propellant is contacted with spontaneous catalyst or non-spontaneous property catalyst, occurs orderly catalysis
Decomposition reaction.
Preferably, the propellant is Hydrazine fuel or catalytic reaction class A fuel A.
Preferably, the single group member liquid-propellant rocket engine radial direction chuck catalyst bed uses radial direction chuck form.
Preferably, the single group member liquid-propellant rocket engine radial direction chuck catalyst bed uses multi-pore channel structure, using sharp
Light, chemically or mechanically progress duct formation or the combining form using large aperture screening.
Compared with prior art, the present invention has following beneficial effect：The present invention is as a result of radially three-dimensional knot
Structure, under physical dimension permanence condition, effectively reduces single group member liquid engine catalyst bed bed load, improves the catalytic bed longevity
Life；Radial direction jacket type structure is employed simultaneously, center hollow out effectively reduces engine weight, and improve engine working process
The problems such as middle spray face temperature is high.Achieve the beneficial effects such as high-thrust single constituent element liquid-propellant rocket engine steady state operating mode.
Brief description of the drawings
By reading the detailed description made with reference to the following drawings to non-limiting example, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the structural representation of single group member liquid-propellant rocket engine radial direction chuck catalyst bed of the present invention.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in figure 1, single group member liquid-propellant rocket engine radial direction chuck catalyst bed of the present invention is by radial integrated formula spray
Device 1, demarcation strip 2, baffle plate 3, upper cover plate 4, lower cover 5 are linked in sequence successively forms and is formed inner ring and outer ring, inner ring with
Outer ring is designed with n independent decomposition chambers, and common 2n decomposition chamber, n is the natural number more than 2, and each independent decomposition chamber of inner ring can be added
Spontaneous catalyst 11, each independent decomposition chamber in outer ring can add spontaneous catalyst 11 or non-spontaneous property catalyst 12, inner ring with
The quantity of outer ring plenum chamber is typically equal, while keeping consistent with the injection into orbit pipe quantity of radial integrated formula injection device.
Spontaneous catalyst or non-spontaneous property catalyst enter each independent decomposition chamber by radially uniform spray, so carry
High stability and speed.It is anti-that propellant completes orderly catalytic decomposition under spontaneous catalyst or non-spontaneous property catalyst action
Should, high-temperature fuel gas is generated, realizes that chemical energy is converted to heat energy, rear high-temperature fuel gas realizes heat energy to kinetic energy by spray Bottomhole pressure
Conversion, is finally sprayed by spout and forms thrust.Radial integrated formula injection device is sprayed after propellant, is formed under the effect of the pressure
Certain initial velocity, jet direction is cylindrical radial, and propellant is contacted with spontaneous catalyst or non-spontaneous property catalyst, had
The cartalytic decomposition effect of sequence.Cartalytic decomposition effect releases big calorimetric, and propellant is under good thermal environment effect, reaction aggravation.
Chamber pressure is set up in short time high temperature combustion gas in thrust chamber, and combustion gas is sprayed through jet pipe effect by spout forms thrust.Using Internal and external cycle
Absolute construction, can add finely grained catalyst in inner ring, be favorably improved engine resistant and oscillation resistant ability, outer ring can selectively add
Enter spontaneous or non-spontaneous property catalyst, reduce engine cost；Using many separate chamber structures, engine work can be effectively reduced
Due to void effect that catalyst attrition is brought during work, it is ensured that engine health reliably working；While catalyst of the present invention
The more conventional monopropellant engine design of heat dispersal situations of bed structure is more friendly, radially jacket structured under identical physical dimension
The catalyst bed bed load of single group member liquid-propellant rocket engine can be effectively reduced, contributes to the big of single group member liquid-propellant rocket engine
Steady operation in the range of thrust design and big flow.
Propellant can be Hydrazine fuel or catalytic reaction class A fuel A, so reduce cost, and reaction is abundant.
Single group member liquid-propellant rocket engine radial direction chuck catalyst bed of the present invention can use radial direction chuck form, so tie
Structure is simple, improves stability.
Single group member liquid-propellant rocket engine radial direction chuck catalyst bed of the present invention can use multi-pore channel structure, can use
Laser, chemically or mechanically progress duct are formed, it would however also be possible to employ the combining form of large aperture screening, prevent catalyst loss
Drop.
The present invention, can be under conditions of ensureing that physical dimension is constant, significantly by the change of catalyst bed configurations form
Degree reduction catalytic bed bed load, so that ensure single group member liquid-propellant rocket engine reliable operation, life-span increase.High-thrust single constituent element
The design research and development of liquid-propellant rocket engine, propose rigors to engine structure size, are only capable of by corresponding catalyst
Bed structure design optimization realizes the high thrust of single group member liquid-propellant rocket engine, and radial direction chuck catalyst bed configurations are identical
Physical dimension under can effectively reduce the bed load of single group member liquid-propellant rocket engine, reduce catalyst breakage rate, improve hair
Motivation overall work thermal environment, improves engine performance.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (6)
1. a kind of single group member liquid-propellant rocket engine radial direction chuck catalyst bed, it is characterised in that the single group member liquid rocket
Engine radial direction chuck catalyst bed is by radial integrated formula injection device, demarcation strip, baffle plate, upper cover plate, lower cover successively by suitable
Sequence is formed by connecting and forms inner ring and outer ring, and inner ring and outer ring are designed with n independent decomposition chambers, common 2n decomposition chamber, n for more than
2 natural number, each independent decomposition chamber of inner ring can add spontaneous catalyst, and each independent decomposition chamber in outer ring can add spontaneous catalysis
Agent or non-spontaneous property catalyst, inner ring are typically equal with the quantity of outer ring plenum chamber, while keeping with radial integrated formula spray dress
The injection into orbit pipe quantity put is consistent.
2. single group member liquid-propellant rocket engine radial direction chuck catalyst bed according to claim 1, it is characterised in that described
Spontaneous catalyst or non-spontaneous property catalyst enter each independent decomposition chamber by radially uniform spray.
3. single group member liquid-propellant rocket engine radial direction chuck catalyst bed according to claim 1, it is characterised in that described
Radial integrated formula injection device is sprayed after propellant, forms certain initial velocity under the effect of the pressure, and jet direction is cylinder footpath
To propellant is contacted with spontaneous catalyst or non-spontaneous property catalyst, occurs orderly cartalytic decomposition effect.
4. single group member liquid-propellant rocket engine radial direction chuck catalyst bed according to claim 3, it is characterised in that described
Propellant is Hydrazine fuel or catalytic reaction class A fuel A.
5. single group member liquid-propellant rocket engine radial direction chuck catalyst bed according to claim 1, it is characterised in that described
Single group member liquid-propellant rocket engine radial direction chuck catalyst bed uses radial direction chuck form.
6. single group member liquid-propellant rocket engine radial direction chuck catalyst bed according to claim 1, it is characterised in that described
Single group member liquid-propellant rocket engine radial direction chuck catalyst bed uses multi-pore channel structure, using laser, chemically or mechanically enters
Row duct is formed or using the combining form of large aperture screening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710348921.0A CN107143433B (en) | 2017-05-17 | 2017-05-17 | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710348921.0A CN107143433B (en) | 2017-05-17 | 2017-05-17 | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107143433A true CN107143433A (en) | 2017-09-08 |
| CN107143433B CN107143433B (en) | 2018-10-30 |
Family
ID=59777538
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710348921.0A Active CN107143433B (en) | 2017-05-17 | 2017-05-17 | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107143433B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109555619A (en) * | 2018-12-30 | 2019-04-02 | 上海空间推进研究所 | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030000200A1 (en) * | 2001-06-29 | 2003-01-02 | Watkins William B. | Gas generator for producing adjustable flow |
| 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 |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN103775246A (en) * | 2014-03-03 | 2014-05-07 | 葛明龙 | Hydrogen peroxide/liquid hydrogen gas generator and thrust chamber |
-
2017
- 2017-05-17 CN CN201710348921.0A patent/CN107143433B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030000200A1 (en) * | 2001-06-29 | 2003-01-02 | Watkins William B. | Gas generator for producing adjustable flow |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| 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 |
| CN103775246A (en) * | 2014-03-03 | 2014-05-07 | 葛明龙 | Hydrogen peroxide/liquid hydrogen gas generator and thrust chamber |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109555619A (en) * | 2018-12-30 | 2019-04-02 | 上海空间推进研究所 | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107143433B (en) | 2018-10-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103775246B (en) | Hydrogen peroxide/liquid hydrogen gas generator and thrust chamber | |
| RU2328615C1 (en) | Liquid-propellant rocket engine chamber mixing head | |
| US5410578A (en) | Nuclear propulsion rocket | |
| RU2007133324A (en) | THREE-COMPONENT SPRAY HEAD FOR OXYGEN-KEROSIN ROCKET ENGINE | |
| CN106939850A (en) | Monopropellant engine anti-backfire injection device | |
| CN104888664B (en) | A kind of self-heating hydrogen supply device and its application | |
| CN103796749A (en) | Catalyst, gas generator, and thruster with improved thermal capability and corrosion resistance | |
| US10563619B2 (en) | Aerospace turbofan engines | |
| CN215109182U (en) | Compound passageway regenerative cooling initiative heat protective structure based on steam reforming | |
| CN113217194B (en) | Composite channel regenerative cooling active heat protection system based on steam reforming | |
| KR101069553B1 (en) | Bipropellant rocket engine using Heat of hydrogen peroxide decomposition and propulsion method thereof | |
| CN107143433B (en) | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed | |
| JP2022553637A (en) | Spacecraft hybrid propulsion system | |
| CN112177801A (en) | Hydrogen peroxide/kerosene rocket engine thrust chamber based on third fluid | |
| Božić et al. | Enhanced development of a catalyst chamber for the decomposition of up to 1.0 kg/s hydrogen peroxide | |
| CN113483354B (en) | Bent truss structure heat shield for afterburner and method for forming air film | |
| RU2663252C1 (en) | Hydrocarbon fuel supply system for hypersonic aircraft and method of fuel supply to system | |
| CN112253335A (en) | Gas generator for driving turbine in rocket engine | |
| CN109555619A (en) | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber | |
| CN111237087A (en) | Novel active and passive micropore plate composite cooling structure for aerospace power and cooling method | |
| CN113982757B (en) | Engine inlet air cooling system | |
| CN215949674U (en) | Electric heating pressurization system for liquid rocket storage tank | |
| US20160229694A1 (en) | Hydrogen peroxide catalyst | |
| CN113882949B (en) | Powder rotary detonation space engine | |
| CN113339162A (en) | High-temperature-resistant pressure-drop-adjustable solid-liquid hybrid rocket engine catalytic bed |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |