CN105971769A - Fuel gas guide device for vertical type test run of small solid rocket engine - Google Patents
Fuel gas guide device for vertical type test run of small solid rocket engine Download PDFInfo
- Publication number
- CN105971769A CN105971769A CN201610550774.0A CN201610550774A CN105971769A CN 105971769 A CN105971769 A CN 105971769A CN 201610550774 A CN201610550774 A CN 201610550774A CN 105971769 A CN105971769 A CN 105971769A
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- China
- Prior art keywords
- solid rocket
- fuel gas
- baffle
- small
- guide body
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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
-
- 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
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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 provides a fuel gas guide device for vertical type test run of a small solid rocket engine. The fuel gas guide device is composed of a guide body and a support; the support is formed by assembling and welding steel plates located on the outer side of the guide body; a steel wire reinforced net is welded inside the support; the guide body is formed by pouring cement resistant to high temperature into the support; a section curve of the guide surface, facing a jet nozzle of the solid rocket engine, of the guide body is composed of an arc line section and a straight line section in a vertical plane, and the straight line section is a tangent line at the tail end of the lower part of the arc line section; upward protrusion edges are arranged on the two sides of the guide surface of the guide body. Through the guide body with the guide surface, gas flow of the jet nozzle of the small solid rocket engine is guided and is led out in the horizontal direction instead of the vertical direction, and therefore facilities and equipment of test beds are protected against ablation caused by high-temperature fuel gas, and the fuel gas and combustion residues are prevented from vertically bouncing and influencing the engine.
Description
Technical field
The present invention relates to Solid Rocket Engine Test technical field, be a kind of for the most vertical examination of solid propellant rocket
Car carries out the device of gas diversion, is specially a kind of small-scale solid rocket motor positive vertical test gas diversion device.
Background technology
During the positive vertical test of solid propellant rocket, from high temperature, the high-speed fuel gas stream direction perpendicular to the ground of jet pipe ejection.Mesh
The most vertical test-bed body of solid propellant rocket of front domestic employing is in order to meet the needs installing the frocks such as running support, testing stand
Surface is steel plate material, when bearing high temperature, the injection of high-speed fuel gas stream, may corrode because of combustion gas stream and cause test-bed body
It is damaged.For preventing high-temperature fuel gas from damaging stage body facility, equipment, anti-after avoiding combustion gas and combustion residue impact ground simultaneously
The bullet impact on electromotor, must guide engine gas, and being allowed to become horizontal direction from vertical direction derives.
In available data, the domestic method that there is no the solid propellant rocket special gas diversion of positive vertical test and facility,
External when building special large-sized solid block testing stand, use " the vertical guiding gutter+cooling pond of steel " mode, but
Which brings water environment pollution, and steel guiding gutter easy-to-rust, need to often overhaul.In addition solid engines combustion gas belongs to gas-solid
Two phase flow, is different from the gas phase combustion gas stream of liquid-propellant rocket engine, baffle contact surface is had strong souring, it is impossible to adopt
With liquid-propellant rocket engine vertical test method of river diversion.
In GB, national military standard, this kind of device is had no requirement.
Summary of the invention
It is an object of the invention to the combustion gas of positive for small-scale solid rocket motor vertical test to be changed direction, with level
Direction is derived, and to prevent high-temperature fuel gas ablation test stage body facility, equipment, avoids combustion gas and combustion residue vertically to rebound simultaneously
Electromotor is impacted.A kind of small-scale solid rocket motor positive vertical test gas diversion device is proposed for this present invention,
Guiding engine gas, being allowed to become horizontal direction from vertical direction derives.
The technical scheme is that
Described a kind of small-scale solid rocket motor positive vertical test gas diversion device, it is characterised in that: by baffle and
Support forms；Described support is formed by the steel plate installed-welded being in outside baffle；Internal stent welding wire reinforcing mat；Baffle
It is cast in internal stent by high temperature resistant cement to be formed；Baffle is vertically being put down towards the guide face of solid propellant rocket nozzle
Cross section curve in face is arc and straightway composition, and wherein straightway is arc lower end tangent line；Baffle water conservancy diversion
There is protrusion edge upwards the both sides in face.
Further preferred version, described a kind of small-scale solid rocket motor positive vertical test gas diversion device, it is special
Levy and be: described air deflector is fixedly mounted on small-scale solid rocket motor positive vertical test test-bed body, and the most flat
In face, solid propellant rocket nozzle axis is not more than 30 ° with the angle of the cross section curve of guide face.
Further preferred version, described a kind of small-scale solid rocket motor positive vertical test gas diversion device, it is special
Levy and be: the inverse proportion function curve that described arc uses coefficient to be 1.
Beneficial effect
The present invention proposes a kind of small-scale solid rocket motor positive vertical test gas diversion device, by with guide face
Baffle, guides the tail gaseous blast of small-sized fixing rocket engine, and being allowed to become horizontal direction from vertical direction derives,
Thus prevent high-temperature fuel gas ablation test stage body facility, equipment, avoid combustion gas and combustion residue vertically to rebound to starting simultaneously
Impacting of machine.
The additional aspect of the present invention and advantage will part be given in the following description, and part will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage are from combining the accompanying drawings below description to embodiment and will become
Substantially with easy to understand, wherein:
Fig. 1: a kind of small-scale solid rocket motor positive vertical test gas diversion device schematic diagram；
The A direction view of Fig. 2: Fig. 1；
Wherein: 1, small-scale solid rocket motor combustion gas stream；2, baffle；3, support；4, guide face cross section curve；5, convex
Go out edge.
Detailed description of the invention
Embodiments of the invention are described below in detail, and described embodiment is exemplary, it is intended to be used for explaining the present invention, and
It is not considered as limiting the invention.
The most domestic when carrying out the most vertical test of solid propellant rocket, the direct perpendicular acting of engine gas stream is to examination
Testing on stage body, test-bed body is the needs meeting and installing the frocks such as running support, and its surface is steel plate material, is bearing high temperature, height
During quick burning jet-impingement, may corrode because of combustion gas stream and cause test-bed body to be damaged.For preventing high-temperature fuel gas from damaging platform
Body facility, equipment, rebound after avoiding combustion gas and combustion residue impact ground the impact on electromotor simultaneously.The present invention proposes
A kind of small-scale solid rocket motor positive vertical test gas diversion device, guides engine gas, is allowed to from vertically side
Derive to becoming horizontal direction.
As it is shown in figure 1, small-scale solid rocket motor positive vertical test gas diversion device is made up of baffle and support.Institute
State support to be formed by the steel plate installed-welded being in outside baffle；Internal stent welding wire reinforcing mat；Baffle is by high-temperature resistant water
Mud is cast in internal stent and is formed, thus baffle forms an entirety with support.
In order to effectively guide combustion gas stream, baffle is erecting towards the guide face of solid propellant rocket nozzle
Cross section curve in straight plane is designed as being made up of arc and straightway, and wherein straightway is arc lower end tangent line.
Being calculated by design, arc preferably employs the inverse proportion function curve y=1/x that coefficient is 1.
There is protrusion edge upwards the both sides of baffle guide face, form outer edge, prevent combustion gas from outwards stretching.
This small-scale solid rocket motor positive vertical test gas diversion device is fixedly mounted on small-scale solid rocket motor
On positive vertical test test-bed body, in order to ensure guide effect, prevent combustion gas and combustion residue bounce-back to electromotor and its
Impacting of his testing equipment, air deflector installation site requires: in perpendicular, solid propellant rocket nozzle axis
Be not more than 30 ° with the angle of the cross section curve of guide face, i.e. nozzle axis has intersection point with the cross section curve of guide face, crosses and hands over
Point does the tangent line of guide face cross section curve, and this tangent line is not more than 30 ° with the angle of nozzle axis.
Although above it has been shown and described that embodiments of the invention, it is to be understood that above-described embodiment is example
Property, it is impossible to be interpreted as limitation of the present invention, those of ordinary skill in the art is without departing from the principle of the present invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, revise, replace and modification.
Claims (3)
1. a small-scale solid rocket motor positive vertical test gas diversion device, it is characterised in that: by baffle and support group
Become；Described support is formed by the steel plate installed-welded being in outside baffle；Internal stent welding wire reinforcing mat；Baffle is by resistance to height
Warm water mud is cast in internal stent and is formed；Baffle towards the guide face of solid propellant rocket nozzle in perpendicular
Cross section curve is arc and straightway composition, and wherein straightway is arc lower end tangent line；The two of baffle guide face
There is protrusion edge upwards side.
A kind of small-scale solid rocket motor positive vertical test gas diversion device, it is characterised in that:
Described air deflector is fixedly mounted on small-scale solid rocket motor positive vertical test test-bed body, and in perpendicular, Gu
Body rocket engine nozzle axis is not more than 30 ° with the angle of the cross section curve of guide face.
A kind of small-scale solid rocket motor positive vertical test gas diversion device, it is characterised in that:
The inverse proportion function curve that described arc uses coefficient to be 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550774.0A CN105971769B (en) | 2016-07-13 | 2016-07-13 | The positive vertical test gas diversion device of small-scale solid rocket motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550774.0A CN105971769B (en) | 2016-07-13 | 2016-07-13 | The positive vertical test gas diversion device of small-scale solid rocket motor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105971769A true CN105971769A (en) | 2016-09-28 |
| CN105971769B CN105971769B (en) | 2017-07-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610550774.0A Active CN105971769B (en) | 2016-07-13 | 2016-07-13 | The positive vertical test gas diversion device of small-scale solid rocket motor |
Country Status (1)
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| CN (1) | CN105971769B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107131794A (en) * | 2017-07-04 | 2017-09-05 | 北京理工大学 | A kind of truck-mounted missile launches double-arc shape air deflector |
| CN107144170A (en) * | 2017-07-04 | 2017-09-08 | 北京理工大学 | A kind of big cambered surface air deflector of monoblock type for Vertical Launch duplex multiple missile |
| CN107202515A (en) * | 2017-07-04 | 2017-09-26 | 北京理工大学 | One kind turns to twist research platform gas diversion device |
| CN108177747A (en) * | 2017-11-09 | 2018-06-19 | 沪东中华造船(集团)有限公司 | A kind of naval vessel sourceless seism rocket projectile fixed transmission air deflector |
| CN108760324A (en) * | 2018-06-13 | 2018-11-06 | 中航工程集成设备有限公司 | A kind of wave absorber of solid propellant rocket underwater test |
| CN108760326A (en) * | 2018-07-24 | 2018-11-06 | 西安近代化学研究所 | A kind of solid engines bump test clamp device |
| CN109050783A (en) * | 2018-08-31 | 2018-12-21 | 中国运载火箭技术研究院 | A kind of disturbing flow device and spoiler of autonomous disturbance triggering Transitional And Turbulent Flow |
| CN111219267A (en) * | 2018-11-23 | 2020-06-02 | 北京航天试验技术研究所 | High-temperature high-speed jet flow deflection device |
| CN111219268A (en) * | 2019-11-29 | 2020-06-02 | 北京航天试验技术研究所 | Engine gas guiding device for spacecraft ground test |
| CN114486266A (en) * | 2021-12-29 | 2022-05-13 | 中国航天空气动力技术研究院 | Space heat-proof structure for aeroengine outdoor posture test run |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107131794A (en) * | 2017-07-04 | 2017-09-05 | 北京理工大学 | A kind of truck-mounted missile launches double-arc shape air deflector |
| CN107144170A (en) * | 2017-07-04 | 2017-09-08 | 北京理工大学 | A kind of big cambered surface air deflector of monoblock type for Vertical Launch duplex multiple missile |
| CN107202515A (en) * | 2017-07-04 | 2017-09-26 | 北京理工大学 | One kind turns to twist research platform gas diversion device |
| CN107131794B (en) * | 2017-07-04 | 2018-11-23 | 北京理工大学 | A kind of truck-mounted missile transmitting double-arc shape air deflector |
| CN108177747A (en) * | 2017-11-09 | 2018-06-19 | 沪东中华造船(集团)有限公司 | A kind of naval vessel sourceless seism rocket projectile fixed transmission air deflector |
| CN108760324A (en) * | 2018-06-13 | 2018-11-06 | 中航工程集成设备有限公司 | A kind of wave absorber of solid propellant rocket underwater test |
| CN108760326A (en) * | 2018-07-24 | 2018-11-06 | 西安近代化学研究所 | A kind of solid engines bump test clamp device |
| CN109050783A (en) * | 2018-08-31 | 2018-12-21 | 中国运载火箭技术研究院 | A kind of disturbing flow device and spoiler of autonomous disturbance triggering Transitional And Turbulent Flow |
| CN111219267A (en) * | 2018-11-23 | 2020-06-02 | 北京航天试验技术研究所 | High-temperature high-speed jet flow deflection device |
| CN111219268A (en) * | 2019-11-29 | 2020-06-02 | 北京航天试验技术研究所 | Engine gas guiding device for spacecraft ground test |
| CN114486266A (en) * | 2021-12-29 | 2022-05-13 | 中国航天空气动力技术研究院 | Space heat-proof structure for aeroengine outdoor posture test run |
Also Published As
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|---|---|
| CN105971769B (en) | 2017-07-04 |
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