CN111156103A - Method and device for accelerating rolling storage process of solid rocket engine - Google Patents
Method and device for accelerating rolling storage process of solid rocket engine Download PDFInfo
- Publication number
- CN111156103A CN111156103A CN201910584241.8A CN201910584241A CN111156103A CN 111156103 A CN111156103 A CN 111156103A CN 201910584241 A CN201910584241 A CN 201910584241A CN 111156103 A CN111156103 A CN 111156103A
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- engine
- solid rocket
- rocket engine
- storage process
- deformation
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- 239000007787 solid Substances 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000005096 rolling process Methods 0.000 title claims abstract description 25
- 238000003860 storage Methods 0.000 title claims abstract description 21
- 238000012360 testing method Methods 0.000 claims abstract description 30
- 230000001133 acceleration Effects 0.000 claims abstract description 23
- 239000002360 explosive Substances 0.000 claims description 12
- 238000009413 insulation Methods 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 abstract description 5
- 239000003380 propellant Substances 0.000 abstract description 5
- 238000010998 test method Methods 0.000 abstract description 4
- 238000001514 detection method Methods 0.000 abstract description 3
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000011160 research Methods 0.000 abstract description 2
- 230000005484 gravity Effects 0.000 description 6
- 238000005259 measurement Methods 0.000 description 3
- 239000004449 solid propellant Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 238000002513 implantation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003550 marker Substances 0.000 description 1
- 239000003190 viscoelastic substance Substances 0.000 description 1
Images
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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to a test method of a solid rocket engine, in particular to a monitoring test method for accelerating the grain and bonding interface of a large solid rocket in a rolling process. The technical scheme is that the method for accelerating the rolling storage process of the solid rocket engine is characterized in that: the centrifugal acceleration is increased to a certain extent when the solid rocket engine is stored in a rolling way; and a device for an acceleration test in the rolling storage process of the solid rocket engine is designed, so that the creep deformation and the radial tensile stress generated in the rolling storage process of the solid rocket engine are accelerated, and the debonding speed of the interface of the propellant and the heat insulating layer is accelerated. The invention has the characteristics of high acceleration speed and high detection precision, and can provide technical support for the research and optimization of the roll period of the engine.
Description
Technical Field
The invention relates to a test method of a solid rocket engine, in particular to a monitoring test method for accelerating the grain and bonding interface of a large solid rocket in a rolling process.
Background
As the most important component of solid rocket engines, the grains are made of solid propellant. The solid propellant is a viscoelastic material, when the solid rocket engine is horizontally stored for a long time, the grain can creep under the action of self gravity to cause the change of a combustion surface, and meanwhile, the interface above the combustion chamber barrel section generates radial tensile stress, so that the propellant is debonded from the interface of the heat insulating layer, or the original debonding is further continuously expanded. Therefore, the storage performance of solid rocket engines depends mainly on the storage characteristics of the grains and their interfaces.
In order to avoid the above situations, the prior art adopts a method of rolling the engine at a certain angle at regular intervals to relieve the creep of the explosive column and recover the stress of the bonding interface, but the measure can increase a large amount of service work, improve the guarantee difficulty and the maintenance cost, and bring inconvenience to the use of products.
Aiming at the problem of guaranteeing the use of the engine by the existing rolling, the change rule of the interface stress and the grain deformation in the rolling period is researched, the rolling angle and the optimal rolling period of the engine are optimized, and the method has important significance for improving the guarantee performance of equipment.
Disclosure of Invention
The invention aims to provide an accelerating method for a rolling storage process of a solid rocket engine, which accelerates the creep deformation and the radial tensile stress generated during the rolling storage of the solid rocket engine so as to accelerate the debonding speed of a propellant and a heat insulating layer interface; and the corresponding relation between the acceleration condition and the natural storage condition is established, so that the deformation of the explosive column and the change of the interface stress in the rolling storage process can be obtained in a short time, and conditions are provided for researching the deformation rule of the explosive column and the change rule of the interface stress in the rolling period.
The technical scheme of the invention is as follows: a method for accelerating the rolling storage process of a solid rocket engine is characterized by comprising the following steps: the centrifugal acceleration is increased to a certain extent when the solid rocket engine is stored in a rolling way.
A solid rocket engine rolling storage process accelerating device is characterized in that: the system comprises a centrifugal generating device, an engine and a counterweight, wherein the engine is a solid rocket engine to be accelerated; the centrifugal generating device is used for generating a certain acceleration to the engine; the counterweight is used for dynamically balancing with the engine.
Further, the device also comprises a high-rigidity mandrel, a stress sensor, a deformation sensor and a grain deformation test ball; the high-rigidity mandrel is made of a high-modulus material, penetrates through a star hole of the engine and is fixedly connected with the engine; the powder column deformation test ball is a hard light ball and is arranged at a certain position on the surface of the engine powder column (the position is determined by a person skilled in the art); the deformation sensor is fixedly arranged on the high-rigidity mandrel and corresponds to the position of the explosive column deformation test ball, and is used for measuring the displacement of the explosive column deformation test ball; and a measuring meter of the stress sensor is flush with the engine grain.
Further, the installation position of the stress sensor is reserved in a heat insulation layer (also called a lining layer) of the engine.
Furthermore, the deformation sensor is composed of three mutually perpendicular laser range finders, and the distance measuring directions of the three laser range finders pass through the center of the drug column deformation test ball.
The invention has the characteristics of high acceleration speed and high detection precision, and can provide technical support for the research and optimization of the roll period of the engine.
Drawings
FIG. 1 is a schematic diagram of an engine roll storage acceleration test system;
FIG. 2 is a schematic view of monitoring the stress of the bonding interface of the engine and the deformation of the explosive column;
fig. 3 is a schematic view of centrifugal force.
In the figure: the device comprises a balance weight 1, a centrifugal generating device 2, an integrated collecting system 3, a rotating table rotating shaft 4, an engine 5, an engine axis 6, an engine grain 7, an engine shell 8, an engine heat insulating layer/lining layer 9, a grain deformation spherical identification point 10, a grain deformation monitoring sensor test line 11, an interface sensor test line 12, an engine high-rigidity mandrel 13, an interface stress sensor 14 and a grain deformation monitoring sensor group 15.
Detailed Description
The technical scheme of the invention is further specifically described with reference to the accompanying drawings and specific embodiments.
The acceleration test system for the horizontal rolling process of the solid rocket engine shown in fig. 1 and 2 comprises a set of acceleration device, a set of bonding interface stress test system and a set of explosive column deformation test device. The acceleration device simulates the influence of gravity in the rolling process of the engine by improving the acceleration; the bonding stress test system measures the change of the interface stress at a typical position; the charge deformation system measures the deformation of the typical position of the charge.
For interface sensor implantation and tensile/compressive/shear stress measurements, sensor dimensions: not more than phi 10 multiplied by 4mm, tensile and compressive stress range: -1 to 1MPa, shear stress range: 0 to 800 KPa;
for mounting and deformation measurement of the creep sensor, sensor dimensions: not more than 50X 50mm, measurement range: 0 plus or minus 5, and the resolution ratio is 5 um;
the method is also suitable for the acceleration test of the vertical storage process of the solid rocket engine.
The creep model of the propellant grain and the interface can be described by a Soderberg theoretical model, and the creep model under normal stress is as follows:
εc＝Aσntmincreasing stress may increase creep. When the centrifugal test is used to accelerate the deformation of the grain, the distances R from each part on the engine to the original point are different, and the stress sigma caused by the centrifugal acceleration is m omega2R, (omega is rotation)Angular velocity, R is radius of gyration), same creep εcThe relationship between gravity-induced creep and acceleration-induced creep can be expressed as:
obtaining a gravity-induced creep time tgAnd the creep time t of the methodωThe relation is as follows:
in order to reduce the influence of the factor, the invention needs R to be more than or equal to 10R, and the nominal centrifugal acceleration is calculated by the axial position of the engine.
In order to realize horizontal accelerated storage under the condition of simulating an engine with a certain diameter of 200mm for 6 months, the creep characteristic parameter n of the propellant is measured to be 4.5, m is 0.5, the gyration radius R is 2m, and if the rotation angular velocity is 3rad/s, the centrifugal acceleration is 18m/s2The gravity acceleration g is 9.8m/s2Substituting the formula for calculation, the simulated gravity effect test can be completed within 18.2 hours.
The detailed implementation steps are as follows:
●, reserving a sensor mounting position when manufacturing a heat insulation layer/lining 9 of the engine 5, implanting a stress sensor 14 to ensure that a sensor testing surface is flush with an interface to be tested, leading out a testing line 12 through the inside of the heat insulation layer/lining 9, and reliably connecting;
● casting solid propellant, curing to obtain a grain 7 for the engine, and firmly installing a grain deformation test ball 10 as a detection point at a characteristic position;
● fixing a three-dimensional deformation sensor 15 on the high-rigidity mandrel 13, and fixing the three-dimensional deformation sensor in the star hole of the engine 5, so that the three-dimensional deformation sensor group 15 can monitor the displacement change of the marker point 10 of the grain deformation test ball and ensure the reliable connection of the test circuit 11;
● the integrated acquisition system 3, the engine 5 and the counterweight 1 are installed on the centrifugal generating device 2, the rotation radius (the distance from the axle center of the centrifugal generating device to the axis 6 of the engine) is set to be 2m, and the stress sensor test circuit 11 and the deformation sensor test circuit 12 are connected to the integrated acquisition system 3 to ensure the normal work of the test equipment.
● the centrifugal force generating device 2 is turned on to a set rotational speed of 3rad/s and the centrifugal force generating device is rotated around the rotational table shaft 4.
● after working stably, the interface stress and the deformation of the grain are monitored by two kinds of sensors.
● to set point 18.2 hours, centrifuge tester 2 was shut down.
● disassemble the engine 5, counterweight 1 and integrated acquisition system 3.
● the test is complete.
The above detailed description of the present invention is only used for illustrating the present invention and is not limited to the technical solutions described in the embodiments of the present invention, and it should be understood by those skilled in the art that the present invention can be modified or substituted equally to achieve the same technical effects; as long as the use requirements are met, the method is within the protection scope of the invention.
Claims (5)
1. A method for accelerating the rolling storage process of a solid rocket engine is characterized by comprising the following steps: the centrifugal acceleration is increased to a certain extent when the solid rocket engine is stored in a rolling way.
2. A solid rocket engine rolling storage process accelerating device is characterized in that: the system comprises a centrifugal generating device (2), an engine (5) and a counterweight (1), wherein the engine (5) is a solid rocket engine to be accelerated; the centrifugal generating device (2) is used for generating a certain acceleration to the engine; the counterweight (1) is used for dynamically balancing with the engine (5).
3. A solid rocket engine rollover storage process acceleration device as defined in claim 2, characterized in that: the device also comprises a high-rigidity mandrel (13), a stress sensor (14), a deformation sensor (15) and a grain deformation test ball (10); the high-rigidity mandrel (4) is made of a high-modulus material, penetrates through a star hole of the engine and is fixedly connected with the engine; the explosive column deformation testing ball (10) is a hard light ball and is arranged at a certain position on the surface of the explosive column of the engine (5); the deformation sensor (15) is fixedly arranged on the high-rigidity mandrel (13) and corresponds to the position of the explosive column deformation testing ball (10) and is used for measuring the displacement of the explosive column deformation testing ball (10); and the measuring meter of the stress sensor (5) is flush with the explosive column of the engine (5).
4. A solid rocket engine rollover storage process acceleration device as defined in claim 3, characterized in that: and the installation position of the stress sensor (6) is reserved in the heat insulation layer (9) of the engine.
5. A solid rocket engine rollover storage process acceleration device as defined in claim 4, characterized in that: the deformation sensor (15) is composed of three laser range finders which are perpendicular to each other and the distance measuring directions of which pass through the center of the powder column deformation test ball (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910584241.8A CN111156103B (en) | 2019-07-01 | 2019-07-01 | Acceleration method and device for solid rocket engine rolling storage process |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910584241.8A CN111156103B (en) | 2019-07-01 | 2019-07-01 | Acceleration method and device for solid rocket engine rolling storage process |
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| CN111156103A true CN111156103A (en) | 2020-05-15 |
| CN111156103B CN111156103B (en) | 2023-11-14 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493509A (en) * | 2022-10-21 | 2022-12-20 | 湖北航天化学技术研究所 | Solid propellant structure deformation monitoring and detecting device and method based on displacement sensing |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262541A (en) * | 1979-03-28 | 1981-04-21 | The United States Of America As Represented By The Secretary Of The Navy | Method of age testing rubber based propellants |
| US20130043352A1 (en) * | 2011-08-18 | 2013-02-21 | Patrick R.E. Bahn | Throttleable propulsion launch escape systems and devices |
| CN104792540A (en) * | 2015-05-21 | 2015-07-22 | 中国工程物理研究院总体工程研究所 | Centrifugal overload test system of solid rocket engine |
| CN105403474A (en) * | 2015-10-29 | 2016-03-16 | 中国兵器工业第五九研究所 | Natural acceleration testing device and method of composite solid propellant |
| CN107044914A (en) * | 2017-03-16 | 2017-08-15 | 中国人民解放军海军航空工程学院 | Solid engines bonding interface loaded state supervises detection means |
| CN109578169A (en) * | 2018-11-27 | 2019-04-05 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket dynamic centrifugal overload point fire test device and test method |
| CN210422804U (en) * | 2019-07-01 | 2020-04-28 | 中国人民解放军96901部队24分队 | Acceleration device for rolling storage process of solid rocket engine |
-
2019
- 2019-07-01 CN CN201910584241.8A patent/CN111156103B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262541A (en) * | 1979-03-28 | 1981-04-21 | The United States Of America As Represented By The Secretary Of The Navy | Method of age testing rubber based propellants |
| US20130043352A1 (en) * | 2011-08-18 | 2013-02-21 | Patrick R.E. Bahn | Throttleable propulsion launch escape systems and devices |
| CN104792540A (en) * | 2015-05-21 | 2015-07-22 | 中国工程物理研究院总体工程研究所 | Centrifugal overload test system of solid rocket engine |
| CN105403474A (en) * | 2015-10-29 | 2016-03-16 | 中国兵器工业第五九研究所 | Natural acceleration testing device and method of composite solid propellant |
| CN107044914A (en) * | 2017-03-16 | 2017-08-15 | 中国人民解放军海军航空工程学院 | Solid engines bonding interface loaded state supervises detection means |
| CN109578169A (en) * | 2018-11-27 | 2019-04-05 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket dynamic centrifugal overload point fire test device and test method |
| CN210422804U (en) * | 2019-07-01 | 2020-04-28 | 中国人民解放军96901部队24分队 | Acceleration device for rolling storage process of solid rocket engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493509A (en) * | 2022-10-21 | 2022-12-20 | 湖北航天化学技术研究所 | Solid propellant structure deformation monitoring and detecting device and method based on displacement sensing |
| CN115493509B (en) * | 2022-10-21 | 2025-08-22 | 湖北航天化学技术研究所 | A solid propellant structural deformation monitoring device and method based on displacement sensing |
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| CN111156103B (en) | 2023-11-14 |
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