CN109882316A - Length adjustable catalytic bed for monopropellant rocket engine - Google Patents
Length adjustable catalytic bed for monopropellant rocket engine Download PDFInfo
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- CN109882316A CN109882316A CN201910126766.7A CN201910126766A CN109882316A CN 109882316 A CN109882316 A CN 109882316A CN 201910126766 A CN201910126766 A CN 201910126766A CN 109882316 A CN109882316 A CN 109882316A
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- heat insulation
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- spring
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Abstract
The present invention provides a kind of length adjustable catalytic beds for monopropellant rocket engine, including decomposition chamber, partition, heat insulation cylinder, spring, heat insulation loop；The front end of decomposition chamber is connected to the ejector filler of engine, receives the injection of propellant；The rear end of decomposition chamber is connected to the jet pipe of engine, and the gas after being catalytically decomposed is sprayed through the jet pipe；Partition is arranged in decomposition chamber, partition by the catalytic bed along axially spaced at external crucible, rear bed, be placed with catalyst respectively in the external crucible, rear bed；Heat insulation cylinder is mounted in decomposition chamber, decomposition chamber is divided into catalytic bed chamber, spring mattress bed chamber, spring setting is intracavitary in spring mattress bed；Spring mattress bed chamber is internally provided with heat insulation loop.The present invention can eliminate or reduce the catalytic bed cavity of nontoxic monopropellant engine, to increase engine startup temperature number, extend the engine long-term steady-state working time, significantly improve the service life and functional reliability of engine.
Description
Technical field
The present invention relates to the engine arts of spacecraft propulsion system, and in particular, to one kind is used for single group member rocket
The length adjustable catalytic bed of engine, eliminated more particularly, to a kind of nontoxic monopropellant engine applied to carrier rocket or
The band for reducing cavity holds out against the unit group engine catalysis bed structure design of spring.
Background technique
Catalytic bed is the core component of nontoxic monopropellant engine, and propellant is evaporated in catalytic bed, is catalytically decomposed
With burning etc. reaction, form the combustion gas of high temperature and pressure, sprayed through jet pipe supersonic speed, to generate thrust needed for spacecraft.Nothing
The performance and functional reliability of malicious unit engine largely depend on the design of catalytic bed.
Currently, catalyst breakage is more serious after engine is repeated several times starting and works long hours.Catalyst breakage is tighter
Weight, catalytic bed cavity is bigger, bigger to chemical reaction and heat transfer and the adverse effect of mass transfer, and the service life of engine is shorter, weight
The multiple number of starts is fewer, and reliability is lower.Therefore, it eliminates or reduction catalytic bed cavity can significantly improve nontoxic single group member and start
The repetition startup temperature number and working life of machine.
The prior art relevant to the application is patent document CN106134388B, proposes a kind of nontoxic monopropellant
Monopropellant engine, the engine is by thrust chamber and solenoid valve block at thrust chamber is made of ejector filler and body portion.Body portion includes two
Layer catalytic bed and combustion chamber, catalytic bed, the external crucible of catalytic bed use finely grained catalyst, and rear bed uses coarse granule catalyst.It adopts
The active constituent of catalyst is metal iridium, and amount containing iridium is between 5%-35%.There is a combustion chamber behind catalytic bed.Front and back
Between catalytic bed, there is the refractory metal net for adding coating between catalytic bed and combustion chamber and add the refractory metal porous plate of coating.
Solenoid valve is opened, and nontoxic monopropellant is sprayed from ejector filler, is catalytically decomposed by catalytic bed, the combustion of decomposition product and propellant
Material, into jet pipe, generates thrust after combustion chambers burn.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of length for monopropellant rocket engine
Adjustable catalytic bed.
A kind of length adjustable catalytic bed for monopropellant rocket engine provided according to the present invention, including decompose
Room, partition, heat insulation cylinder, spring, heat insulation loop；The front end of decomposition chamber is connected to the ejector filler of engine, receives the injection of propellant；
The rear end of decomposition chamber is connected to the jet pipe of engine, and the gas after being catalytically decomposed is sprayed through the jet pipe；Partition setting is dividing
Solution is indoor, partition by the catalytic bed along axially spaced at external crucible, rear bed, be placed with catalyst respectively in the external crucible, rear bed；
Heat insulation cylinder is mounted in decomposition chamber, decomposition chamber is divided into catalytic bed chamber, spring mattress bed chamber, spring setting is intracavitary in spring mattress bed；Spring
Bed chamber is internally provided with heat insulation loop.
Preferably, catalytic bed chamber is inserted into one end of the heat insulation cylinder, and the other end of heat insulation cylinder is located at spring mattress bed chamber；The bullet
Spring can push heat insulation cylinder to move to catalytic bed chamber.
Preferably, the material of the decomposition chamber has high temperature resistance, the material and the propellant and catalyst energy
It is enough compatible.
Preferably, the decomposition chamber shape is round or annular.The section phase of the cross section of the partition and decomposition chamber
Together, the axial surface of partition is uniformly distributed several holes, and the material of partition has high temperature resistance, the material and the propulsion
Agent and catalyst can be compatible.
Preferably, heat insulating coat is coated in the surface of the heat insulation cylinder, the part of the heat insulation cylinder insertion catalytic bed chamber
Axial surface is uniformly distributed several holes, and the material of heat insulation cylinder has a high temperature resistance, the material and the propellant and urges
Agent can be compatible.
Preferably, the material of the spring has fire-resistant oxidation resistant performance, and the elastic force of spring, which is greater than, resists catalytic bed chamber
The pressure that flow resistance generates, so that the cavity generated after catalyst breakage is extruded or eliminates.
Preferably, the heat insulation loop is arranged between heat insulation cylinder and spring, and the spring can hold out against heat insulation cylinder.It is described every
The internal diameter of hot ring is greater than the outer diameter of heat insulation cylinder, and the outer diameter of heat insulation loop is less than the internal diameter of spring.
Preferably, the material of the decomposition chamber is iron-based wrought superalloy, ni-base wrought superalloy, cobalt-based deformation height
Any one of temperature alloy, niobium alloy, stainless steel, platinum-rhodium alloy, platinumiridio, iridium-rhodium alloy, rhenium iridium alloy or tantalum-tungsten alloy.
Compared with prior art, the present invention have it is following the utility model has the advantages that
Engine catalytic bed is designed as spring bed structure, so that since catalyst breakage produces in engine working process
Raw cavity can be eliminated or reduce immediately, and to being promoted, engine repeats startup temperature number and the performance that works long hours is with important
Meaning.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is schematic structural cross-sectional view of the invention；
Fig. 2 is structure two dimension view of the invention, and arrow indicates propellant flow direction in figure.
It is shown in figure: decomposition chamber 11；Partition 12；Heat insulation cylinder 13；Spring 14；Heat insulation loop 15.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
In order to improve the repetition startup temperature number and working life of nontoxic monopropellant engine, the present invention provides a kind of use
In the catalysis bed structure design of rocket engine prevention cavity, the catalytic bed of engine is designed to an adjustable in length formula
Catalytic bed, the catalytic bed that can be effectively reduced engine and generate due to leading to catalyst breakage because repeating startup temperature and working long hours are empty
Chamber meets requirement of the existing nontoxic monopropellant engine to this startup temperature and long-life reliably working.
A kind of length adjustable catalytic bed for monopropellant rocket engine provided according to the present invention, including decomposition chamber
11, partition 12, heat insulation cylinder 13, spring 14, heat insulation loop 15；
The front end of decomposition chamber 11 is connected to the ejector filler of engine, receives the injection of propellant；
The rear end of decomposition chamber 11 is connected to the jet pipe of engine, and the gas after being catalytically decomposed is sprayed through the jet pipe；
Partition 12 be arranged in decomposition chamber 11, partition 12 by the catalytic bed along axially spaced at external crucible, rear bed, before described
It is placed with catalyst respectively in bed, rear bed；
Heat insulation cylinder 13 is mounted in decomposition chamber 11, decomposition chamber 11 is divided into catalytic bed chamber, spring mattress bed chamber, the setting of spring 14 exists
Spring mattress bed is intracavitary；
Spring mattress bed chamber is internally provided with heat insulation loop 15.
Specifically, catalytic bed chamber is inserted into one end of the heat insulation cylinder 13, and the other end of heat insulation cylinder 13 is located at spring mattress bed chamber；Institute
Stating spring 14 can push heat insulation cylinder 13 to move to catalytic bed chamber.
Specifically, the material of the decomposition chamber 11 has high temperature resistance, the material and the propellant and catalyst
It can be compatible.
Specifically, 11 shape of decomposition chamber is round or annular.
Specifically, the cross section of the partition 12 is identical as the section of decomposition chamber 11, and the axial surface of partition 12 uniformly divides
Several holes of cloth, the material of partition 12 have high temperature resistance, and the material can be compatible with the propellant and catalyst.
Specifically, heat insulating coat is coated in the surface of the heat insulation cylinder 13, and the heat insulation cylinder 13 is inserted into the portion of catalytic bed chamber
The axial surface divided is uniformly distributed several holes, and the material of heat insulation cylinder 13 has high temperature resistance, the material and the propulsion
Agent and catalyst can be compatible.Spring mattress bed chamber and heat insulation cylinder have carried out heat insulating coat and ceramic insulation design, to reduce engine
Influence of the high temperature to 14 coefficient of elasticity of spring when work.The heat-insulated barrel structure runs through entire spring mattress bed, and surface is coated heat-insulated
Coating, insertion catalytic bed part axial surface are uniformly distributed several identical apertures of diameter, make inside spring mattress bed decomposition chamber
It is separated into two cavitys of catalytic bed and spring mattress bed.
Specifically, the material of the spring 14 has fire-resistant oxidation resistant performance, and the elastic force of spring 14, which is greater than, resists catalysis
The pressure that bed chamber flow resistance generates, so that the cavity generated after catalyst breakage is extruded or eliminates.Preferably, before engine operation
The compressed shape variable of spring 14 is maximum, it is desirable that the maximum elastic force that spring 14 provides at this time is not enough to crush catalyst；Engine work
After spring mattress bed eliminates cavity during work, the compressed shape variable of spring 14 reduces, the minimum elastic force for requiring spring 14 to provide at this time
It is enough to resist the thrust of catalytic bed flow resistance generation.
Specifically, the heat insulation loop 15 is arranged between heat insulation cylinder 13 and spring 14, and the spring 14 can hold out against heat-insulated
Cylinder 13.
Specifically, the internal diameter of the heat insulation loop 15 is greater than the outer diameter of heat insulation cylinder 13, and the outer diameter of heat insulation loop 15 is less than spring 14
Internal diameter.Preferably, the heat insulation loop 15 is mounted between heat insulation cylinder 13 and spring 14, and the internal diameter of heat insulation loop 15 is slightly larger than heat-insulated
The outer diameter of cylinder 13, the outer diameter of heat insulation loop 15 are slightly less than the internal diameter of spring mattress bed chamber.
Specifically, the material of the decomposition chamber 11 is iron-based wrought superalloy, ni-base wrought superalloy, cobalt-based deformation
Any in high temperature alloy, niobium alloy, stainless steel, platinum-rhodium alloy, platinumiridio, iridium-rhodium alloy, rhenium iridium alloy or tantalum-tungsten alloy
Kind, and can have compatibility with the propellant, catalyst and the combustion gas of generation of rocket engine.
The course of work of the catalytic bed is that, for the cavity generated after the catalyst breakage in engine, heat insulation cylinder exists
It is moved under the action of spring force to the decomposition chamber of catalytic bed, eliminates or reduce cavity.Spring mattress bed decomposition chamber is separated by heat insulation cylinder,
Front is to decompose chamber, and rear portion is spring mattress bed chamber.Perforation before and after entire spring mattress bed decomposition chamber, so that propellant is direct from ejector filler
Catalytic bed is sprayed into, catalytic decomposition burning gases flow through spring mattress bed chamber, spray through jet pipe.The catalytic bed is placed in engine spray
After device, before jet pipe.
In the particular embodiment, as shown in Fig. 2, spring mattress bed decomposes the heat insulation cylinder 13 of indoor location, decomposition chamber is divided into
Catalytic bed chamber is inserted into one end of catalytic bed chamber and spring mattress bed chamber, heat insulation cylinder 13, prevents catalyst from entering spring mattress bed chamber and jet pipe.Every
The other end of hot cylinder 13 is located at spring mattress bed chamber, and spring 14 is installed between spring mattress bed decomposition chamber and heat insulation cylinder, so that heat insulation cylinder can
It is mobile to catalytic bed under the promotion of spring, the cavity generated by catalyst breakage is eliminated or reduced, the temperature of engine is improved
The number of starts and long steady state operation life.The surfaces externally and internally and spring mattress bed inner cavity surface of heat insulation cylinder 13 have carried out Design on thermal insulation, table
There is heat insulating coat in face, and interior design has heat insulation loop 15, can be effectively reduced the temperature of spring, avoids high temperature to spring system
Several influences guarantees that spring effectively works.
The catalytic bed and conventional structure catalytic bed of the present embodiment is respectively adopted, has carried out heat run test, to investigate ratio
The performance of more different structure engines.It is learnt by test data, the engine of conventional structure can only be startup temperature 150 times or so,
The catalytic bed structure engine startup temperature number for preventing cavity can reach 500 times or more, be conventional structure more than 3 times, and press
Force curve shock range is small, illustrates that engine performance is more steady.
After the present invention is implemented on the nontoxic monopropellant engine of spacecraft propulsion system, it is capable of providing a kind of nontoxic list
Constituent element engine catalytic bed leads to the problem of cavity to eliminate or reduce existing nontoxic monopropellant engine catalytic bed, overcomes existing
There is structure to be difficult to repeatedly start the defect of work on the engine.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of length adjustable catalytic bed for monopropellant rocket engine, which is characterized in that including decomposition chamber (11), every
Plate (12), heat insulation cylinder (13), spring (14), heat insulation loop (15)；
The front end of decomposition chamber (11) is connected to the ejector filler of engine, receives the injection of propellant；
The rear end of decomposition chamber (11) is connected to the jet pipe of engine, and the gas after being catalytically decomposed is sprayed through the jet pipe；
Partition (12) setting in the decomposition chamber (11), partition (12) by the catalytic bed along axially spaced at external crucible, rear bed, it is described
It is placed with catalyst respectively in external crucible, rear bed；
Heat insulation cylinder (13) is mounted in decomposition chamber (11), decomposition chamber (11) is divided into catalytic bed chamber, spring mattress bed chamber, spring (14) is set
It sets intracavitary in spring mattress bed；
Spring mattress bed chamber is internally provided with heat insulation loop (15).
2. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
One end insertion catalytic bed chamber of heat insulation cylinder (13) is stated, the other end of heat insulation cylinder (13) is located at spring mattress bed chamber；
The spring (14) can push heat insulation cylinder (13) to move to catalytic bed chamber.
3. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
The material for stating decomposition chamber (11) has high temperature resistance, and the material can be compatible with the propellant and catalyst.
4. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
Stating decomposition chamber (11) shape is round or annular.
5. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
The cross section for stating partition (12) is identical as the section of decomposition chamber (11), and the axial surface of partition (12) is uniformly distributed several holes,
The material of partition (12) has high temperature resistance, and the material can be compatible with the propellant and catalyst.
6. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
Heat insulating coat is coated in the surface for stating heat insulation cylinder (13), and the axial surface of the part of heat insulation cylinder (13) the insertion catalytic bed chamber is equal
Even several holes of distribution, the material of heat insulation cylinder (13) have high temperature resistance, the material and the propellant and catalyst energy
It is enough compatible.
7. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
The material for stating spring (14) has fire-resistant oxidation resistant performance, and the elastic force of spring (14), which is greater than, resists what catalytic bed chamber flow resistance generated
Pressure, so that the cavity generated after catalyst breakage is extruded or eliminates.
8. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that institute
It states heat insulation loop (15) to be arranged between heat insulation cylinder (13) and spring (14), the spring (14) can hold out against heat insulation cylinder (13).
9. the length adjustable catalytic bed according to claim 8 for monopropellant rocket engine, which is characterized in that institute
The internal diameter for stating heat insulation loop (15) is greater than the outer diameter of heat insulation cylinder (13), and the outer diameter of heat insulation loop (15) is less than the internal diameter of spring (14).
10. the length adjustable catalytic bed according to claim 1 for monopropellant rocket engine, which is characterized in that
The material of the decomposition chamber (11) is iron-based wrought superalloy, ni-base wrought superalloy, cobalt-based wrought superalloy, niobium conjunction
Any one of gold, stainless steel, platinum-rhodium alloy, platinumiridio, iridium-rhodium alloy, rhenium iridium alloy or tantalum-tungsten alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910126766.7A CN109882316B (en) | 2019-02-20 | 2019-02-20 | Length-adjustable catalytic bed for single-component rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910126766.7A CN109882316B (en) | 2019-02-20 | 2019-02-20 | Length-adjustable catalytic bed for single-component rocket engine |
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| Publication Number | Publication Date |
|---|---|
| CN109882316A true CN109882316A (en) | 2019-06-14 |
| CN109882316B CN109882316B (en) | 2020-05-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910126766.7A Active CN109882316B (en) | 2019-02-20 | 2019-02-20 | Length-adjustable catalytic bed for single-component rocket engine |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134388B (en) * | 2010-12-10 | 2013-12-11 | 上海空间推进研究所 | A kind of monopropellant engine of nontoxic monopropellant |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN104153914A (en) * | 2014-07-23 | 2014-11-19 | 北京控制工程研究所 | Thrust chamber for ADN (ammonium dinitramide)-based non-toxic thruster and welding technology of thrust chamber |
-
2019
- 2019-02-20 CN CN201910126766.7A patent/CN109882316B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134388B (en) * | 2010-12-10 | 2013-12-11 | 上海空间推进研究所 | A kind of monopropellant engine of nontoxic monopropellant |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN104153914A (en) * | 2014-07-23 | 2014-11-19 | 北京控制工程研究所 | Thrust chamber for ADN (ammonium dinitramide)-based non-toxic thruster and welding technology of thrust chamber |
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| Publication number | Publication date |
|---|---|
| CN109882316B (en) | 2020-05-29 |
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