CN106121862A - A kind of solid rocket motor grain fixing device - Google Patents
A kind of solid rocket motor grain fixing device Download PDFInfo
- Publication number
- CN106121862A CN106121862A CN201610658368.6A CN201610658368A CN106121862A CN 106121862 A CN106121862 A CN 106121862A CN 201610658368 A CN201610658368 A CN 201610658368A CN 106121862 A CN106121862 A CN 106121862A
- Authority
- CN
- China
- Prior art keywords
- positioning sleeve
- circlip
- pad
- fixing device
- rocket motor
- 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.)
- Pending
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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
- F02K9/08—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
- F02K9/36—Propellant charge supports
-
- 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 solid rocket motor grain fixing device, for stationary engine full surface combustion powder column in stability radially.Motor grain fixing device includes positioning sleeve, circlip, pad.Positioning sleeve is thin slice circular configuration, uses replaceable part design, mates different size of positioning sleeve respectively according to the difference of projectile charge diameter.Multiple circlips are uniformly distributed along positioning sleeve circumference, it is ensured that the stability of powder charge axis.Being provided with circular arc pad in the end of positioning sleeve inner elastic back-up ring, many group circlip pads are equal according to positioning sleeve center of circle radial distance, can reduce stress and concentrate the destructiveness to powder charge.Positioning sleeve and circlip, pad all use same kind refractory metal material to process；In combustion, it is ensured that the parastate of free loading propellant full surface combustion powder column axis, put-put is carried out more accurately at ground pressure and thrust testing experiment.
Description
Technical field
The invention belongs to solid propellant rocket standing test technical field, specifically, relate to a kind of solid-rocket and send out
Motivation powder column fixing device.
Background technology
Engines ground pressure and thrust testing experiment occupy critically important ground in solid propellant rocket development process
Position.At present, in put-put pressure with thrust testing experiment, basic employing free loading propellant full surface combustion powder column.Pass through
A large amount of test data show, full surface combustion powder column is in engine operating duration, and powder column revolving body axis cannot stably be put down
Row is on burning chamber shell axis so that bias phenomenon occur in the pressure of electromotor and thrust curve, it is therefore necessary to eliminate this
Plant test error that is not parallel due to powder column axis and that cause.At present in small-scale solid rocket motor, for free loading propellant
The radial stability of full surface combustion powder column lacks a kind of simple and effective strutting means, and patent of invention 201210440049.X carries
Go out " electromotor in a kind of big L/D ratio rocket engine running support " and patent of invention 201110321594.2 disclosure " a kind of use
In solid propellant rocket standing test slide tube type centre frame " in stationary engine in existing problems be: just for solid fire
Arrow electromotor housing parts in ground static test run is tested proposes fixing device and method of attachment, not in housing
Charge segment launch research.Patent 201320430843.6 proposes " a kind of rocket propellant grain fixing device ", to medicine
In the research of column fixer, weak point is: powder column is axially proposed a kind of fixation, but to Miniature solid rocket
In electromotor, the radially fixed of full surface combustion powder charge need research.And in terms of powder charge production, disclosed document " little opening
The free powder column of housing is fixed " (" play arrow with guidance journal ", 2009,01:157-158.) proposes several in production technology mistake
Corrective measure to fixation in journey, but do not discuss for powder column stability in housing.
Summary of the invention
The deficiency existed in order to avoid prior art, the present invention proposes a kind of solid rocket motor grain fixing device.
The technical solution adopted for the present invention to solve the technical problems is: include positioning sleeve, circlip, pad, described
Positioning sleeve is thin slice cirque structure, has multiple installing hole according to the center of circle is the most circumferentially distributed, and described circlip is respectively mounted
On positioning sleeve, 1/3rd of circlip are positioned at outside positioning sleeve, and 2/3rds are positioned at inside positioning sleeve, and pad is arranged on
The end of positioning sleeve inner elastic back-up ring, positioning sleeve, circlip, pad coordinate, are used for fixing full surface combustion powder column in footpath
To stability.
Described circlip circumferentially distributed at least three along positioning sleeve；Circlip powder charge burning before in by compressed shape
State.
Described pad is circular arc, and many group pads are equal according to center of circle radial distance.
Positioning sleeve and circlip, pad all use same kind refractory metal material.
Beneficial effect
The present invention propose solid rocket motor grain fixing device, from the mounting means of circlip it can be seen that
(1) positioning sleeve takes replaceable part to design, according to the difference of small-scale solid rocket motor charge diameter size
Mate different size of centring ring respectively.
(2) circlip uses multiple being uniformly distributed, and can farthest ensure the stability of powder charge axis, not affect
The volume of powder charge in thrust chamber is filled, and reduces the probability of the rough burning produced.
(3) in circlip inside end, circular arc pad is installed, stress can be reduced and concentrate the destruction to powder charge
Probability.
(4) in combustion, it is ensured that the parastate of free loading propellant full surface combustion powder column axis, carry out more accurately
Put-put is at ground pressure and thrust testing experiment.
Accompanying drawing explanation
With embodiment, one solid rocket motor grain fixing device of the present invention is made further below in conjunction with the accompanying drawings
Describe in detail.
Fig. 1 is solid rocket motor grain fixture structure schematic diagram of the present invention.
Fig. 2 is solid rocket motor grain fixing device side view of the present invention.
Fig. 3 is small-scale solid rocket motor pressure-time graph.
Fig. 4 is that small-scale solid rocket motor pushes away force-time curve.
Fig. 5 is small-scale solid rocket motor characteristic velocity matched curve.
Fig. 6 is small-scale solid rocket motor thrust coefficient matched curve.
In figure:
1. positioning sleeve 2. circlip 3. pad
Detailed description of the invention
The present embodiment is a kind of solid rocket motor grain fixing device.
After Design of Solid Propellant Rocket Engine completes, ground static experiment to be carried out, measure pressure-time graph and push away
Force-time curve, then carries out data process, and whether Examined effect index reaches to design requirement.Without reaching, also to enter
One step Amending design, carries out ground experiment again, until it reaches design requirement.In order to obtain the pressure-time graph of electromotor
With push away force-time curve, by installing pressure transducer on the engine and thrust pickup, by tested pressure and thrust
Signal is changed into voltage signal, and voltage signal is amplified to be preserved by computer data acquisition system.Due to sensor output
Be voltage signal, and test that to need obtain be thrust and pressure signal, i.e. real physical, therefore before experiment, reply is used
Sensor demarcate, the purpose of demarcation is the relation in order to set up between sensor voltage signal and real physical, only
Be input in computer acquisition system by calibration result, when signals collecting, acquisition system will will record according to calibration result
The signal of telecommunication be converted into real physical, pressure-time graph and push away force-time curve can be obtained.If at test process
Middle use free loading propellant full surface combustion powder column axially in parallel degree instability, then can affect the pressure in combustor and thrust becomes
Change, make test result and design conditions have very large deviation, so farthest to ensure small-scale solid rocket motor ground
The free loading propellant full surface combustion powder column axial degree of stability in combustor in static experiment.
Refering to Fig. 1～Fig. 6, the present embodiment solid rocket motor grain fixing device, by positioning sleeve 1, circlip 2,
Pad 3 forms；Positioning sleeve 1 is thin slice cirque structure, has multiple installing hole according to the center of circle is the most circumferentially distributed, and positioning sleeve 1 is big
Smaller diameter root is tested the diameter difference of middle-size and small-size rocket engine cast factually and is changed, and the very thin thickness of positioning sleeve 1, no
Extra thrust chamber volume can be taken.When using the solid engines housing of different-diameter size, need to manufacture difference
The powder column fixing device of specification, to ensure that positioning sleeve 1 is in stability radially.Circlip 2 is separately mounted on positioning sleeve 1,
/ 3rd of circlip 2 are positioned at outside positioning sleeve 1, and 2/3rds of circlip 2 are positioned at inside positioning sleeve 1, elastic gear
Circle 2 is confined state before powder charge is burnt, and ensures the depth of parallelism of powder charge axis due to elastic reaction in powder charge combustion process
There is not large change.In the present embodiment, positioning sleeve 1 is provided with three circlips 2.The effect of circlip 2 is to ensure that
When small-scale solid rocket motor uses free loading propellant full surface combustion powder column, test whole process in ground static test run
In, the axis of powder column and housing axis most of the time are maintained in a depth of parallelism.Pad 3 is circular arc, and pad 3 is arranged on
The end of positioning sleeve inner elastic back-up ring 2；Positioning sleeve 1, circlip 2, pad 3 coordinate, and are used for fixing full surface combustion powder column
In stability radially.Pad 3 in use direct surface combustion powder column complete with free loading propellant connects, it is to avoid stress collection
In the medicine column crack even powder column Fragmentation Phenomena that causes.Additionally, the arc length of pad can not be long when concrete Application Design,
Owing to burning tip fixing device can be the most stuck, long camber line can cause powder column radial stability to be deteriorated.
In the present embodiment, positioning sleeve 1, circlip 2 and pad 3 all use same kind refractory metal material to process.
With avoid high-temperature, High Voltage combustor in by high-temperature fuel gas ablation, may result in the shakiness of pressure inner trajectory curve
Standing wave is dynamic or nozzle throat blocks.Ensure the using effect of motor grain fixing device, multiple device can be used simultaneously to fix
Powder column, is separately mounted to powder column head, middle part and afterbody.When the free loading propellant full surface combustion powder column afterbody afterburnt, afterbody
Fixing device lost efficacy, but the fixing device of middle part and head still can guarantee that the radial stability of powder column, reduced Small Solid fire
The rough burning phenomenon of arrow electromotor.
The present embodiment solid rocket motor grain fixture structure parameter:
Degree of packing 1.65kg/m3；External diameter is 14mm；Internal diameter is 11mm；Chamber length is 200mm；Black powder uses 7
Gram No. 2 black powders of granule；Powder charge uses SQ-2 type medicine.
Based on above-mentioned solid rocket motor grain fixing device, the full surface of test free loading propellant used in the present embodiment
The small-scale solid rocket motor fast cookof method of burning powder column, sequentially includes the following steps:
(1) electromotor prepares: checks and overlaps each parts and components of electromotor and motor grain fixing device together, measuring jet pipe
Larynx footpath；
(2) main charge prepares: check powder column outer surface quality, estimates calculating and weighs powder column quality；
(3) ignition charge prepares: weighs No. 2 black powders of 7 grams of granules, and makees an igniter pad；
(4) checking experiment data collecting system, Iganition control system；
(5) by each for electromotor parts, main charge, igniter pad assembling；By motor grain fixing device and electromotor
Interior powder column coordinates to be installed, and is arranged on test bay by the electromotor assembled；
(6) pressure transducer and thrust pickup are installed on the engine；
(7) duty of each test equipment is checked；
(8) personal security is left between experiment, junction point live wire, closes iron gate between experiment；
(9) check igniting resistance, check again for the duty of each test equipment, set data collecting system, wait
Trigger；
(10) sending out firing command, engine ignition works, and acquisition system carries out the collection of data in experimentation, preserves institute
The experimental data collected；
(11) dismantle electromotor of participating in the experiment, clean out and be coated with antirust oil, complete experiment.
Claims (4)
1. a solid rocket motor grain fixing device, it is characterised in that: include positioning sleeve, circlip, pad, described
Positioning sleeve is thin slice cirque structure, has multiple installing hole according to the center of circle is the most circumferentially distributed, and described circlip is respectively mounted
On positioning sleeve, 1/3rd of circlip are positioned at outside positioning sleeve, and 2/3rds are positioned at inside positioning sleeve, and pad is arranged on
The end of positioning sleeve inner elastic back-up ring, positioning sleeve, circlip, pad coordinate, are used for fixing full surface combustion powder column in footpath
To stability.
Solid rocket motor grain fixing device the most according to claim 1, it is characterised in that: described circlip edge
Circumferentially distributed at least three of positioning sleeve；Circlip powder charge burn before in confined state.
Solid rocket motor grain fixing device the most according to claim 1, it is characterised in that: described pad is circular arc
Shape, many group pads are equal according to center of circle radial distance.
Solid rocket motor grain fixing device the most according to claim 1, it is characterised in that: positioning sleeve and elastic gear
Circle, pad all use same kind refractory metal material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610658368.6A CN106121862A (en) | 2016-08-11 | 2016-08-11 | A kind of solid rocket motor grain fixing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610658368.6A CN106121862A (en) | 2016-08-11 | 2016-08-11 | A kind of solid rocket motor grain fixing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106121862A true CN106121862A (en) | 2016-11-16 |
Family
ID=57258481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610658368.6A Pending CN106121862A (en) | 2016-08-11 | 2016-08-11 | A kind of solid rocket motor grain fixing device |
Country Status (1)
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| CN (1) | CN106121862A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107965399A (en) * | 2017-12-07 | 2018-04-27 | 上海新力动力设备研究所 | A kind of powder column of resistance to ablation support plate for being applicable in free loading propellant solid propellant rocket |
| CN109404164A (en) * | 2018-09-17 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of charge constitution that solid propellant rocket combustibility improves |
| CN110966116A (en) * | 2019-11-08 | 2020-04-07 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN110985236A (en) * | 2019-12-30 | 2020-04-10 | 西安航科等离子体科技有限公司 | Supporting device and supporting method for end face combustion explosive column of solid rocket engine |
| CN112211748A (en) * | 2020-10-14 | 2021-01-12 | 西北工业大学 | Wheel block type explosive column capable of simultaneously burning inside and outside |
| CN112377327A (en) * | 2020-10-20 | 2021-02-19 | 北京控制工程研究所 | Gas generating agent grain fixing structure of solid cold gas generator for space |
| CN112610359A (en) * | 2020-12-28 | 2021-04-06 | 中国航天空气动力技术研究院 | Solid rocket engine fixing device of embedded installation |
| CN113482798A (en) * | 2021-06-22 | 2021-10-08 | 南阳北方向东工业有限公司 | Free-packed grain explosive pressing structure of solid rocket engine and use method |
| CN114683445A (en) * | 2022-04-18 | 2022-07-01 | 大连理工大学 | Solid rocket engine disassembly-free wing column type grain forming die and forming method |
| WO2024002034A1 (en) * | 2022-06-30 | 2024-01-04 | 西安航天动力测控技术研究所 | Fixing device for temperature sensors in combustion chamber of solid rocket engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1496990A (en) * | 1965-10-23 | 1967-10-06 | Bolkow Gmbh | Solid fuel rocket thruster |
| US3853058A (en) * | 1972-01-05 | 1974-12-10 | Luchaire Sa | Improvements in or relating to rockets |
| RU2145674C1 (en) * | 1999-06-10 | 2000-02-20 | Пермский завод им.С.М.Кирова | Solid propellant charge |
| CN1302353A (en) * | 1998-05-22 | 2001-07-04 | 罗格·E·洛 | Modular solid fuel rocket propelling charges with a casing, a fill-drain syctem, cooling and suspension |
| CN203499853U (en) * | 2013-07-19 | 2014-03-26 | 晋西工业集团有限责任公司 | Rocket propellant grain fixing device |
-
2016
- 2016-08-11 CN CN201610658368.6A patent/CN106121862A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1496990A (en) * | 1965-10-23 | 1967-10-06 | Bolkow Gmbh | Solid fuel rocket thruster |
| US3853058A (en) * | 1972-01-05 | 1974-12-10 | Luchaire Sa | Improvements in or relating to rockets |
| CN1302353A (en) * | 1998-05-22 | 2001-07-04 | 罗格·E·洛 | Modular solid fuel rocket propelling charges with a casing, a fill-drain syctem, cooling and suspension |
| RU2145674C1 (en) * | 1999-06-10 | 2000-02-20 | Пермский завод им.С.М.Кирова | Solid propellant charge |
| CN203499853U (en) * | 2013-07-19 | 2014-03-26 | 晋西工业集团有限责任公司 | Rocket propellant grain fixing device |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107965399A (en) * | 2017-12-07 | 2018-04-27 | 上海新力动力设备研究所 | A kind of powder column of resistance to ablation support plate for being applicable in free loading propellant solid propellant rocket |
| CN109404164A (en) * | 2018-09-17 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of charge constitution that solid propellant rocket combustibility improves |
| CN109404164B (en) * | 2018-09-17 | 2021-08-03 | 江西洪都航空工业集团有限责任公司 | Charge structure for improving combustion performance of solid rocket engine |
| CN110966116A (en) * | 2019-11-08 | 2020-04-07 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN110985236A (en) * | 2019-12-30 | 2020-04-10 | 西安航科等离子体科技有限公司 | Supporting device and supporting method for end face combustion explosive column of solid rocket engine |
| CN112211748B (en) * | 2020-10-14 | 2022-07-29 | 西北工业大学 | Wheel block type explosive column capable of simultaneously burning inside and outside |
| CN112211748A (en) * | 2020-10-14 | 2021-01-12 | 西北工业大学 | Wheel block type explosive column capable of simultaneously burning inside and outside |
| CN112377327A (en) * | 2020-10-20 | 2021-02-19 | 北京控制工程研究所 | Gas generating agent grain fixing structure of solid cold gas generator for space |
| CN112377327B (en) * | 2020-10-20 | 2021-09-03 | 北京控制工程研究所 | Gas generating agent grain fixing structure of solid cold gas generator for space |
| CN112610359A (en) * | 2020-12-28 | 2021-04-06 | 中国航天空气动力技术研究院 | Solid rocket engine fixing device of embedded installation |
| CN113482798B (en) * | 2021-06-22 | 2022-07-01 | 南阳北方向东工业有限公司 | Free-packed grain pressing structure of solid rocket engine and use method |
| CN113482798A (en) * | 2021-06-22 | 2021-10-08 | 南阳北方向东工业有限公司 | Free-packed grain explosive pressing structure of solid rocket engine and use method |
| CN114683445A (en) * | 2022-04-18 | 2022-07-01 | 大连理工大学 | Solid rocket engine disassembly-free wing column type grain forming die and forming method |
| WO2024002034A1 (en) * | 2022-06-30 | 2024-01-04 | 西安航天动力测控技术研究所 | Fixing device for temperature sensors in combustion chamber of solid rocket engine |
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Effective date of abandoning: 20180403 |