CN110486192A - The connection of dipulse engine ablation test and test device - Google Patents
The connection of dipulse engine ablation test and test device Download PDFInfo
- Publication number
- CN110486192A CN110486192A CN201910761396.4A CN201910761396A CN110486192A CN 110486192 A CN110486192 A CN 110486192A CN 201910761396 A CN201910761396 A CN 201910761396A CN 110486192 A CN110486192 A CN 110486192A
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- China
- Prior art keywords
- test
- test device
- dipulse
- connection
- ablation
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- 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 discloses a kind of connection of dipulse engine ablation test and test device, connection and a test device generally cube structure, three sides are provided with peripheral hardware connecting hole, and the other side sets that there are two instrument connections, and top is provided with oblique 34 ° of fire holes.Using 45 high-intensitive Steel materials, it is ensured that structural strength.Three peripheral hardware connecting holes are equipped with internal screw thread, to connect with external dipulse experiment device；Two instrument connections are equipped with internal screw thread, connect with test macro, carry out real-time monitoring to experiment flow field；Top has an inclined fire hole that igniting combustion gas is made to act directly on powder charge end face.The present invention solves the problems, such as that the soft interlayer ablation test device of Double pulse solid rocket motor assembles and the simulation and observation of subsequent soft interlayer work ablation process.
Description
Technical field
The invention belongs to dipulse engine thermal guard system experimental study fields, specifically, being a kind of dipulse hair
The connection of motivation ablation test and test device.
Background technique
Solid propellant rocket is easy to use because its structure is simple, the good characteristics such as reliable operation, in all kinds of weapon systems
In be widely applied.But with the gradually development of aerospace field, conventional solid rocket engine thrust can not interrupt and
The inherent shortcoming of regulation more highlights, when especially by it compared with the superior controllability of liquid-propellant rocket engine.Therefore, to solid
The research of body rocket engine controllability technology is particularly important.
By the two-way promotion between modernized war and missile weapon system, the newest of Solid Rocket Motor Technology is ground
Study carefully achievement --- Double pulse solid rocket motor comes into being.Dipulse engine has the ability repeatedly started, prominent anti-
Emit outside area, emphasize trajectory changeability, unquestionably, proposes one kind well for the inherent shortcoming of solid propellant rocket
Solution.Solid propellant rocket is divided into two with the grade Time Isolation Unit with anti-flaming thermal-insulation function by dipulse engine
A relatively independent combustion chamber possesses independent ignition system, and control system can control two combustion chambers respectively successively lights a fire and open
It is dynamic, achieve the effect that thrust controllable repeatedly starts.
Combustion chamber needs the thermal force and 10MPa or more of bearing 3000K or more for a long time in dipulse engine working process
Inner pressuring load effect, and with the design of the use of high-energy propellant and high specific impulse engine, moderate pressure is carried in combustion chamber
Lotus will further be promoted.To ensure that dipulse engine reliable works, the soft interlayer of impulsive quarantine device is designed to Guan Chong
It wants, thermal protection struc ture thickness is insufficient, will lead to shell excessive temperature rise, jeopardizes structural intergrity；Conversely, thermal protection struc ture designs redundancy,
Engine passiveness quality will be caused to increase, seriously affect function of the engine.Therefore, it is necessary to design a kind of dipulse engine
Ablation test connection and test device provide reference to the thermal protection structure design of dipulse engine.
Summary of the invention
The purpose of the present invention is to provide a kind of connection of dipulse engine ablation test and test devices, solve double arteries and veins
The problem of soft interlayer ablation test device of solid propellant rocket assembles is rushed, can be realized using the experimental rig connector
Experimental rig assemble and the simulation and observation of subsequent soft interlayer work ablation process.
The technical solution for realizing the aim of the invention is as follows: a kind of connection of dipulse engine ablation test and test dress
It sets, a device generally cube structure, three sides are provided with peripheral hardware connecting hole, and the other side sets that there are two instrument connections, and top is provided with
One inclined fire hole.
Three peripheral hardware connecting holes are equipped with internal screw thread, for connecting with external dipulse experiment device.
In three peripheral hardware connecting holes, two of them peripheral hardware connecting hole is distributed in opposite side, should be in two of opposite side distribution
Connecting hole is coaxial, and aperture is consistent.
Two instrument connection is equipped with internal screw thread, for connecting with test macro.
The fire hole at the top and the gradient of top surface are 34 °.
The fire hole, upper part are the concave station for being 34 ° with top surface tilt angle, and lower part is to set internal thread to lead to
Hole.
Compared with prior art, the present invention its remarkable advantage is:
(1) this connection and test device structure are simple, easy to assembly, to the cavity body structure connected without limitation, meet all kinds of realities
Test condition requirement.
(2) this connection and test device misconvergence expansion segment, can the II soft interlayer of pulse of real simulation dipulse engine
Working condition, help to reappear before soft interlayer the almost flow field of stagnation, hastening phenomenon be not present.
(3) this connection and test device side are provided with instrument connection, can be to the flow field real-time monitoring before soft interlayer, to interlayer
Ablation Analysis provides effectively reference, compensates for the compound working environment of the soft interlayer of II pulse of dipulse engine and is difficult to measure not
Foot.
(4) this connection and test device are equipped with igniter connecting hole, it is ensured that ignition security is reliable.
Detailed description of the invention
Fig. 1 is a kind of dipulse engine ablation test connection of the present invention and test device, wherein (a) is semi-cutaway, (b)
It (c) is side view for A-A cross-sectional view.
Specific embodiment
The invention will be further described below in conjunction with the accompanying drawings.
In conjunction with Fig. 1, a kind of connection of dipulse engine ablation test and test device are passed for studying heat-insulating material mass transfer
Thermal ablation process has important reference value to engine thermal current design manual of protective structures.
The connection and a test device generally cube structure, three sides are provided with peripheral hardware connecting hole, and the other side is equipped with two
A instrument connection, top are provided with oblique 34 ° of fire holes.
Using 45 high-intensitive Steel materials, it is ensured that structural strength.
Three peripheral hardware connecting holes of the connection and test device are equipped with internal screw thread, to fill with external dipulse experiment
Set connection.
The side of the connection and test device is opened there are two instrument connection, and instrument connection is equipped with internal screw thread, is connected with test macro
It connects, real-time monitoring is carried out to experiment flow field.
An inclined fire hole is provided at the top of the connection and test device, upper part is the recessed of same tilt angle
Platform, lower part are to set internal thread through-hole.Tilting fire hole purpose is that igniting combustion gas acts directly on powder charge end face.
Claims (7)
1. a kind of dipulse engine ablation test connection and test device, it is characterised in that: a device generally cube
Structure, three sides are provided with peripheral hardware connecting hole, and the other side sets that there are two instrument connections, and top is provided with an inclined fire hole.
2. dipulse engine ablation test connection according to claim 1 and test device, it is characterised in that: described three
A peripheral hardware connecting hole is equipped with internal screw thread, for connecting with external dipulse experiment device.
3. dipulse engine ablation test connection according to claim 2 and test device, it is characterised in that: described three
In a peripheral hardware connecting hole, two of them peripheral hardware connecting hole is distributed in opposite side, should be coaxial in two connecting holes of opposite side distribution, and hole
Diameter is consistent.
4. dipulse engine ablation test connection according to claim 1 and test device, it is characterised in that: described two
Instrument connection is equipped with internal screw thread, for connecting with test macro.
5. dipulse engine ablation test connection according to claim 1 and test device, it is characterised in that: the top
The fire hole in portion and the gradient of top surface are 34 °.
6. dipulse engine ablation test connection according to claim 5 and test device, it is characterised in that: the point
Fire hole, upper part are the concave station for being 34 ° with top surface tilt angle, and lower part is to set internal thread through-hole.
7. dipulse engine ablation test connection according to claim 1 and test device, it is characterised in that: the device
Using 45 Steel materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910761396.4A CN110486192A (en) | 2019-08-18 | 2019-08-18 | The connection of dipulse engine ablation test and test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910761396.4A CN110486192A (en) | 2019-08-18 | 2019-08-18 | The connection of dipulse engine ablation test and test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110486192A true CN110486192A (en) | 2019-11-22 |
Family
ID=68551931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910761396.4A Pending CN110486192A (en) | 2019-08-18 | 2019-08-18 | The connection of dipulse engine ablation test and test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110486192A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198849A (en) * | 2016-09-14 | 2016-12-07 | 中国科学技术大学 | A kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof |
| CN110082475A (en) * | 2019-04-17 | 2019-08-02 | 西北工业大学 | Simulate the experimental method and experimental provision of Double pulse solid rocket motor ablation |
-
2019
- 2019-08-18 CN CN201910761396.4A patent/CN110486192A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198849A (en) * | 2016-09-14 | 2016-12-07 | 中国科学技术大学 | A kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof |
| CN110082475A (en) * | 2019-04-17 | 2019-08-02 | 西北工业大学 | Simulate the experimental method and experimental provision of Double pulse solid rocket motor ablation |
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| 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 |
Application publication date: 20191122 |
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| RJ01 | Rejection of invention patent application after publication |