CN105971769B - The positive vertical test gas diversion device of small-scale solid rocket motor - Google Patents
The positive vertical test gas diversion device of small-scale solid rocket motor Download PDFInfo
- Publication number
- CN105971769B CN105971769B CN201610550774.0A CN201610550774A CN105971769B CN 105971769 B CN105971769 B CN 105971769B CN 201610550774 A CN201610550774 A CN 201610550774A CN 105971769 B CN105971769 B CN 105971769B
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- China
- Prior art keywords
- baffle
- small
- rocket motor
- straightway
- guide face
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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
Abstract
The present invention proposes a kind of positive vertical test gas diversion device of small-scale solid rocket motor, is made up of baffle and support；Support is formed by the steel plate group weldering on the outside of baffle；Internal stent welding wire reinforcing mat；Baffle is cast in internal stent and is formed by high temperature resistant cement；Baffle is that arc and straightway are constituted towards the cross section curve of the guide face in perpendicular of solid propellant rocket nozzle, and wherein straightway is arc lower end tangent line；There is upward protrusion edge the both sides of baffle guide face.By the baffle with guide face, tail gaseous blast to small-sized fixed rocket engine is guided, it is allowed to be changed into horizontal direction derivation from vertical direction, so as to prevent high-temperature fuel gas ablation test stage body facility, equipment, while avoiding combustion gas and combustion residue, vertically bounce-back is impacted to engine.
Description
Technical field
It is that one kind is used for the just vertical examination of solid propellant rocket the present invention relates to Solid Rocket Engine Test technical field
Car carries out the device of gas diversion, specially a kind of positive vertical test gas diversion device of small-scale solid rocket motor.
Background technology
During the positive vertical test of solid propellant rocket, high temperature, the high-speed fuel gas stream sprayed from jet pipe direction perpendicular to the ground.Mesh
The need for the preceding domestic just vertical test-bed body of solid propellant rocket for using is in order to meet the frocks such as installation running support, testing stand
Body surface face is steel plate material, and when high temperature, the injection of high-speed fuel gas stream is born, may be corroded because of combustion gas stream cause test-bed body
It is damaged.To prevent high-temperature fuel gas from damaging stage body facility, equipment, while anti-after avoiding combustion gas and combustion residue impact ground
Engine gas must be guided by influence of the bullet to engine, be allowed to be changed into horizontal direction derivation from vertical direction.
In available data, the country there is no the method and facility of the solid propellant rocket special gas diversion of positive vertical test,
Foreign countries when special large-sized solid block testing stand is built, using " 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, different from the gas phase combustion gas stream of liquid-propellant rocket engine, has strong souring, it is impossible to adopt to water conservancy diversion contact level
With liquid-propellant rocket engine vertical test method of river diversion.
In GB, national military standard, requirement is had no to this kind of device.
The content of the invention
The purpose of the present invention is the combustion gas of the positive vertical test of small-scale solid rocket motor can be changed into direction, with level
Direction is derived, to prevent high-temperature fuel gas ablation test stage body facility, equipment, while avoiding combustion gas and combustion residue from vertically rebounding
Engine is impacted.For this present invention proposes a kind of positive vertical test gas diversion device of small-scale solid rocket motor,
Engine gas are guided, is allowed to be changed into horizontal direction derivation from vertical direction.
The technical scheme is that：
The positive vertical test gas diversion device of a kind of small-scale solid rocket motor, it is characterised in that：By baffle and
Support is constituted；The support is formed by the steel plate group weldering on the outside of baffle；Internal stent welding wire reinforcing mat；Baffle
Internal stent is cast in by high temperature resistant cement to be formed；Baffle is being put down vertically towards the guide face of solid propellant rocket nozzle
Cross section curve in face is that arc and straightway are constituted, and wherein straightway is arc lower end tangent line；Baffle water conservancy diversion
There is upward protrusion edge the both sides in face.
Further preferred scheme, a kind of positive vertical test gas diversion device of small-scale solid rocket motor, it is special
Levy and be：The air deflector is fixedly mounted on the positive vertical test test-bed body of small-scale solid rocket motor, and is being put down vertically
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 scheme, a kind of positive vertical test gas diversion device of small-scale solid rocket motor, it is special
Levy and be：The arc use coefficient for 1 inverse proportion function curve.
Beneficial effect
The present invention proposes a kind of positive vertical test gas diversion device of small-scale solid rocket motor, by with guide face
Baffle, the tail gaseous blast to small-sized fixed rocket engine is guided, and is allowed to be changed into horizontal direction derivation from vertical direction,
So as to prevent high-temperature fuel gas ablation test stage body facility, equipment, while avoiding combustion gas and combustion residue from vertically rebounding to starting
Machine is impacted.
Additional aspect of the invention and advantage will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by practice of the invention.
Brief description of the drawings
Of the invention above-mentioned and/or additional aspect and advantage will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Fig. 1：A kind of positive vertical test gas diversion device schematic diagram of small-scale solid rocket motor；
Fig. 2：The A direction views of Fig. 1；
Wherein：1st, small-scale solid rocket motor combustion gas stream；2nd, baffle；3rd, support；4th, guide face cross section curve；5th, it is convex
Go out edge.
Specific embodiment
Embodiments of the invention are described below in detail, the embodiment is exemplary, it is intended to for explaining the present invention, and
It is not considered as limiting the invention.
It is domestic when solid propellant rocket just vertical experiment is carried out at present, the direct perpendicular acting of engine gas stream to examination
Test on stage body, the need for test-bed body is to meet the frocks such as installation running support, its surface is steel plate material, is bearing high temperature, height
During quick burning jet-impingement, may be corroded because of combustion gas stream causes test-bed body to be damaged.To prevent high-temperature fuel gas from damaging platform
Body facility, equipment, while avoiding the influence rebounded to engine behind combustion gas and combustion residue impact ground.The present invention is proposed
Engine gas are guided by a kind of positive vertical test gas diversion device of small-scale solid rocket motor, are allowed to from vertical side
Derived to horizontal direction is changed into.
As shown in figure 1, the positive vertical test gas diversion device of small-scale solid rocket motor is made up of baffle and support.Institute
Support is stated to be formed by the steel plate group weldering on the outside of baffle；Internal stent welding wire reinforcing mat；Baffle is by high-temperature resistant water
Mud is cast in internal stent and is formed, so that baffle forms an entirety with support.
In order to effectively be guided to combustion gas stream, baffle is being erected 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.
By design calculate, arc preferably use coefficient for 1 inverse proportion function curve y=1/x.
There is upward protrusion edge the both sides of baffle guide face, form outer edge, prevent combustion gas from outwards stretching.
The positive vertical test gas diversion device of the small-scale solid rocket motor 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 engine and its
His testing equipment is impacted, air deflector installation site requirement：In perpendicular, solid propellant rocket nozzle axis
Be not more than 30 °, i.e. nozzle axis with the angle of the cross section curve of guide face 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 the tangent line is not more than 30 ° with the angle of nozzle axis.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from principle of the invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (3)
1. the positive vertical test gas diversion device of a kind of small-scale solid rocket motor, it is characterised in that：By baffle and support group
Into；The support is formed by the steel plate group weldering on the outside of 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 solid propellant rocket nozzle guide face in perpendicular
Cross section curve is that arc and straightway are constituted, and wherein straightway is arc lower end tangent line, and arc connects with straightway
The arc tangential direction at place is connect for horizontal direction, the direction of straightway is horizontal direction；The both sides of baffle guide face are oriented
On protrusion edge；Combustion gas is changed into the air deflector horizontal direction derivation from vertical direction.
2. the positive vertical test gas diversion device of a kind of small-scale solid rocket motor according to claim 1, it is characterised in that：
The air deflector is fixedly mounted on the positive vertical test test-bed body of small-scale solid rocket motor, 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.
3. the positive vertical test gas diversion device of a kind of small-scale solid rocket motor according to claim 1, it is characterised in that：
The arc use coefficient for 1 inverse proportion function curve.
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 CN105971769A (en) | 2016-09-28 |
| CN105971769B true CN105971769B (en) | 2017-07-04 |
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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 |
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| CN (1) | CN105971769B (en) |
Families Citing this family (10)
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| 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 |
| 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 |
| CN108177747B (en) * | 2017-11-09 | 2020-08-04 | 沪东中华造船(集团)有限公司 | Ship passive interference rocket projectile fixed launching deflector |
| CN108760324B (en) * | 2018-06-13 | 2020-09-01 | 中航工程集成设备有限公司 | Wave absorbing device for underwater test of solid rocket engine |
| 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 |
| CN109050783B (en) * | 2018-08-31 | 2020-02-14 | 中国运载火箭技术研究院 | Flow disturbing device and flow disturbing sheet for autonomous disturbance triggering turbulence flow transition |
| 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 |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6499289B1 (en) * | 2000-03-31 | 2002-12-31 | Alliant Technologies Inc. | Pyrolytic graphite gauge for measuring heat flux |
| US6776049B2 (en) * | 2001-12-07 | 2004-08-17 | Alliant Techsystems Inc. | System and method for measuring stress at an interface |
| CN103743572B (en) * | 2014-01-08 | 2016-01-06 | 北京航空航天大学 | Small rocket motor testing table spray equipment |
| CN104612858B (en) * | 2015-01-29 | 2016-09-21 | 南京理工大学 | Adjustable Double pulse solid rocket motor nozzle test device |
| CN204783326U (en) * | 2015-07-09 | 2015-11-18 | 南京理工大学 | Solid rocket engine ignition test device |
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| CN105971769A (en) | 2016-09-28 |
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