CN111779593A - Solid rocket engine shell, solid rocket engine and manufacturing method thereof - Google Patents
Solid rocket engine shell, solid rocket engine and manufacturing method thereof Download PDFInfo
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- CN111779593A CN111779593A CN202010518436.5A CN202010518436A CN111779593A CN 111779593 A CN111779593 A CN 111779593A CN 202010518436 A CN202010518436 A CN 202010518436A CN 111779593 A CN111779593 A CN 111779593A
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- 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
- F02K9/34—Casings; Combustion chambers; Liners thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
- B29C69/02—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore of moulding techniques only
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- 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
- F02K9/10—Shape or structure of solid propellant charges
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- 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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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B6/00—Light guides; Structural details of arrangements comprising light guides and other optical elements, e.g. couplings
- G02B6/46—Processes or apparatus adapted for installing or repairing optical fibres or optical cables
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
Abstract
The solid rocket engine shell comprises a winding layer, a heat insulation structure, a plurality of optical fibers and a plurality of sensors, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure; the winding layer is wound outside the heat insulation structure. The optical fibers are arranged at intervals along the outer circumference direction of the heat insulation structure, the optical fibers are bonded with the heat insulation structure, each optical fiber comprises a leading-out end and an embedded end, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the bus direction of the heat insulation structure and extend into the powder charging space; the embedded end of the optical fiber is connected with a sensor which is used for monitoring the propellant grain (a charging interface or the inside of the grain). The solid rocket engine comprises a solid rocket engine shell and a propellant grain filled in a charging space.
Description
Technical Field
The application relates to the technical field of solid rocket engines, in particular to a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof.
Background
The prior rocket engine is a common power device for various missile weapons and aerospace vehicles, and the defects of inclusion, pores, layering, interface debonding and the like are easily formed when the engine propellant is cast and molded due to the relatively poor process stability of the composite material. And due to the reasons of temperature, vibration, collision and the like, the defects tend to be expanded continuously in the processes of storage, transportation and use of the engine, if the defects are not monitored and controlled, the problems of 'super' combustion surface and the like of the solid rocket engine during working can be caused, so that the solid rocket engine is greatly threatened, the reliability and the safety of the solid rocket engine are obviously influenced, and serious even serious safety accidents can be caused.
In the related technology, the commonly used monitoring means of the solid rocket engine mainly comprise ultrasonic monitoring, ray monitoring, penetration monitoring and the like, and although the methods are mature in technology, the methods have the defects of monitoring lag, incapability of real-time in-situ monitoring and early warning and the like. Meanwhile, with the increase of the size of the solid rocket engine, the large-size composite material shell has a strong energy attenuation characteristic, the traditional monitoring method is limited in capability and is not suitable any more, and a new means for accurately monitoring the solid rocket engine is urgently needed.
Disclosure of Invention
The embodiment of the application provides a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof, and aims to solve the problems that monitoring of the interior of the solid rocket engine is delayed and real-time in-situ monitoring and early warning cannot be carried out in the related technology.
In a first aspect, there is provided a solid rocket engine casing comprising:
the heat insulation structure is internally provided with a powder charging space for accommodating propellant grains, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;
the optical fibers are arranged at intervals along the outer circumferential direction of the heat insulation structure and comprise leading-out ends and embedded ends, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the generatrix direction of the heat insulation structure and extend into the powder charging space;
the embedded ends of the optical fibers are connected with the sensors, and the sensors are used for monitoring the propellant grains;
a wrap layer wrapped around the insulation structure.
In some embodiments, the insulating structure comprises a column section and a front and a rear head seal section connected to the two ends of the column section, respectively; the light path channel is formed by end faces of the column section and the front end socket section which are connected with each other, and the embedded end extends to be embedded in the light path channel along the bus direction of the front end socket section; and/or, the light path channel is formed by the end surfaces of the column section and the rear head sealing section which are connected with each other, and the embedded end extends to be embedded in the light path channel along the bus direction of the rear head sealing section.
In some embodiments, when the optical channel is formed by end faces of the column section and the front sealing head section, the front sealing head section includes a first section and a second section connected to each other, the second section is connected to the column section, and an upper surface of the second section is disposed obliquely downward to guide the embedded end into the optical channel.
In some embodiments, the column section includes a third section and a fourth section connected to each other, and a thickness of the fourth section gradually decreases from an end close to the third section to an end far from the third section so as to abut on the second section.
In some embodiments, the tilt angle of the second segment is α, 0< α ≦ 30.
In a second aspect, a method of making a solid rocket engine casing is provided, comprising the steps of:
providing a plurality of optical fibers, the optical fibers including a pigtail end and an embedded end;
assembling a heat insulation structure on a winding core mold, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;
arranging all the optical fibers at intervals along the outer circumferential direction of the heat insulation structure, extending leading-out ends of the optical fibers out of the heat insulation structure, and extending embedded ends into the light path channel along the bus direction of the heat insulation structure and extending into the charge space;
winding outside the heat insulation structure to form a winding layer;
and detecting whether all the optical fibers are alive or not, and connecting a sensor at the embedded end of the alive optical fibers to monitor the propellant grain.
In some embodiments, the insulating structure comprises a column section and a front and a rear head seal section connected to the two ends of the column section, respectively; the light path channel is formed by end faces of the column section and the front seal head section which are connected with each other;
the method for assembling the heat insulation structure on the winding core mold specifically comprises the following steps:
preparing the front sealing head section and the rear sealing head section by adopting a compression molding manner;
assembling the front head sealing section and the rear head sealing section on the winding core mould at intervals along the axial direction of the winding core mould;
arranging all the optical fibers at intervals along the outer circumferential direction of the front head sealing section, extending the leading-out ends of the optical fibers out of the front head sealing section, and extending the embedded ends into the charging space along the bus direction of the front head sealing section;
paving a heat insulation segment on the winding core mold between the front head sealing section and the rear head sealing section to form the column section;
the front head seal segment, the column segment, and the rear head seal segment collectively form the insulating structure.
In some embodiments, monitoring whether all of the optical fibers are alive comprises:
connecting an optical fiber jumper at the leading-out end of the optical fiber;
connecting a laser pen with the optical fiber jumper to communicate the optical fiber;
if the embedded end of the optical fiber is bright, judging that the optical fiber is alive; otherwise, judging that the optical fiber is not alive;
and repeating the steps to monitor whether all the optical fibers are alive or not.
In a third aspect, there is provided a solid rocket engine comprising:
the heat insulation structure is internally provided with a powder charging space for accommodating propellant grains, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;
a propellant grain filled in the charge space;
the optical fibers are arranged at intervals along the outer circumferential direction of the heat insulation structure and comprise leading-out ends and embedded ends, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the generatrix direction of the heat insulation structure and extend into the propellant grain;
the embedded ends of the optical fibers are connected with the sensors, and the sensors are used for monitoring the propellant grains;
a wrap layer wrapped around the insulation structure.
In a fourth aspect, a method for manufacturing a solid rocket engine is provided, which comprises the following steps:
providing a plurality of optical fibers, the optical fibers including a pigtail end and an embedded end;
assembling a heat insulation structure on a winding core mold, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;
arranging all the optical fibers at intervals along the outer circumferential direction of the heat insulation structure, extending leading-out ends of the optical fibers out of the heat insulation structure, and extending embedded ends into the light path channel along the bus direction of the heat insulation structure and extending into the charge space;
winding outside the heat insulation structure to form a winding layer;
monitoring whether all the optical fibers survive or not, and connecting a sensor at the embedded end of the surviving optical fibers;
removing the winding core mold;
and spraying a lining layer and pouring a propellant grain in the charging space so as to enable the sensor to extend into the propellant grain and monitor the propellant grain.
The beneficial effect that technical scheme that this application provided brought includes: the optical fiber and the sensor are pre-embedded in the heat insulation structure of the engine to realize in-situ monitoring of the interior of the engine, and the optical fiber is small in diameter (0.25mm), so that an integrated structure is formed after the optical fiber and the heat insulation structure are cured and molded in the process of introducing the optical fiber into the heat insulation structure of the engine, and defects of the heat insulation structure cannot be caused. And can realize on-line, real-time, initiative monitoring and control to the propellant grain inside the heat insulating structure, find and confirm the debonding of propellant grain and heat insulating structure connecting interface in time, the position and degree of the internal crackle of propellant grain, injury, and monitor the expansion of the damaged area, not only can strengthen the engine state prediction ability effectively, reduce the difficulty of engine inspection and trouble discrimination, promote engine life and reliability, still benefit the discovery of the early problem of propellant grain, thus take the remedial measure in time, in order to avoid the emergence of major accident, guarantee the safety and stability of the solid rocket engine.
The embodiment of the application provides a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof, since the optical fiber and the sensor are pre-embedded in the heat insulation structure of the engine, the in-situ monitoring of the interior of the engine is realized, therefore, the method can realize the online, real-time and active monitoring and control of the propellant grain in the heat insulation structure, timely find and determine the debonding of the propellant grain and the connection interface of the heat insulation structure, the position and the degree of cracks and damages in the propellant grain, and monitors the expansion of the damaged area, not only can effectively enhance the engine state prediction capability, reduce the difficulty of engine inspection and fault discrimination, improve the service life and reliability of the engine, but also is beneficial to the discovery of early problems of propellant grains, therefore, remedial measures are taken in time to avoid major accidents and ensure the safety and stability of the solid rocket engine.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural view of a solid rocket engine casing provided in an embodiment of the present application;
FIG. 2 is a schematic structural diagram of a solid rocket engine provided in an embodiment of the present application;
FIG. 3 is a schematic diagram of an embedded state of an optical fiber according to an embodiment of the present disclosure;
fig. 4 is a schematic view illustrating an installation state of a column section according to an embodiment of the present disclosure;
fig. 5 is a schematic view illustrating an installation state of a winding layer according to an embodiment of the present application.
In the figure: 1. an insulating structure; 10. a charge space; 11. a column section; 110. a third stage; 111. a fourth stage; 12. a front seal head section; 120. a first stage; 121. a second stage; 13. a rear head sealing section; 2. a propellant grain; 3. an optical path channel; 4. an optical fiber; 40. leading out the terminal; 41. an embedded end; 5. a sensor; 6. a winding layer; 7. and winding the core mold.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Example 1:
referring to fig. 1, embodiment 1 of the present application provides a solid rocket engine case, which can solve the problems of delayed monitoring and incapability of real-time in-situ monitoring and early warning in the interior of a solid rocket engine in the related art.
The solid rocket engine casing that this application embodiment 1 provided includes adiabatic structure 1, winding layer 6, a plurality of optic fibre 4 and a plurality of sensor 5, it has the powder charge space 10 that is used for accommodating propellant grain 2 in the adiabatic structure 1, and set up the light path passageway 3 along this adiabatic structure 1 circumference extension on the adiabatic structure 1, this light path passageway 3 is the occupation space of optic fibre 4 itself, optic fibre 4 gets into light path passageway 3 after, light path passageway 3 is sealed, optic fibre 4 and adiabatic structure 1 form overall structure. The winding layer 6 is wound around the thermal insulation structure 1. The optical fibers 4 are arranged at intervals along the outer circumference direction of the heat insulation structure 1, the optical fibers 4 are adhered with the heat insulation structure 1, each optical fiber 4 comprises an outgoing end 40 and an embedded end 41, the outgoing end 40 extends out of the heat insulation structure 1, and the embedded end 41 is adhered to the outer surface of the heat insulation structure 1 along the generatrix direction of the heat insulation structure 1 and extends into the medicine containing space 10 along the light path channel 3. Because the optical fiber 4 is tiny in size, the heat insulation structure 1 is integrally formed with the heat insulation structure 1 after being cured, the optical fiber 4 enters the optical path channel 3 and then seals the optical path channel 3, the whole heat insulation structure 1 is seamless, and the stability and the safety of an engine are not influenced. The embedded end 41 of the optical fiber 4 is connected with one or more sensors 5, the sensors 5 are embedded into the propellant charge space 10 in advance, after the propellant grains 2 are poured into the propellant charge space 10, the sensors 5 are embedded into the propellant grains 2, real-time in-situ monitoring can be carried out on the propellant grains 2, monitoring results are timely and reliable, data of changes of the surface and the inside of the propellant grains 2 along with environmental loads such as strain and temperature can be obtained, and the stability and the safety of the engine can be accurately judged.
The optical fiber 4 adopted in the embodiment 1 of the application is small in size, so that the internal structure and the bonding interface of the engine cannot be damaged; the strain range of the optical fiber 4 is large, and the optical fiber can adapt to the strain ranges of the surface and the interior of the propellant grain 2; and the current is not introduced in the measuring process, so that the method has absolute safety and is the best choice for monitoring the health of the solid rocket engine.
The solid rocket engine shell of embodiment 1 of the application realizes in-situ monitoring of the interior of the engine by pre-embedding the optical fiber 4 and the sensor 5, and has the following advantages: as the diameter of the optical fiber 4 is small (0.25mm), the defects of the heat insulation structure 1 and the damage of the optical path channel 3 can not be caused in the process of introducing the optical fiber 4 into the heat insulation structure 1 of the engine. And can realize online, real-time, initiative monitoring and control to propellant powder column 2 inside the heat insulating structure 1, find and confirm debonding, propellant powder column 2 internal crack, damaged position and degree of 2 in propellant powder column of the joint interface of 2 in time and heat insulating structure 1, and monitor the expansion of the damaged area, not merely can strengthen the engine state prediction ability effectively, reduce the difficulty of engine detection and fault discrimination, promote engine life-span and reliability, and facilitate the discovery of the early problem of propellant powder column 2, thus take the remedial measure in time, in order to avoid the emergence of the major accident, guarantee the safety and stability of the solid rocket engine.
Optionally, the heat insulation structure 1 comprises a column section 11, and a front head sealing section 12 and a rear head sealing section 13 respectively connected to two ends of the column section 11; the optical path channel 3 is formed by end faces of the column section 11 and the front head section 12 which are connected with each other, and the embedded end 41 extends to be embedded in the optical path channel 3 along a bus direction of the front head section 12. Optical fiber 4 penetrates in adiabatic structure 1 by the juncture position of preceding seal head section 12 and column segment 11, need not to open light path channel 3 in addition on adiabatic structure 1, and optical fiber 4 is tiny, bond in juncture position department of preceding seal head section 12 and column segment 11 can be as an organic whole structure with preceding seal head section 12 and column segment 11 shaping, after adiabatic structure 1 solidification preceding seal head section 12, bonding interface is totally enclosed between optical fiber 4 and the column segment 11, there is not the gap, do not influence the stability and the security of engine, and just contact with high temperature gas before the juncture position of preceding seal head section 12 and column segment 11 is close to the end at engine work, it is short to have the exposure time, the reliability is high, long advantage in test time range.
Preferably, when the light path channel 3 is formed by the end face where the column section 11 and the front head-sealing section 12 are connected to each other, the front head-sealing section 12 includes a first section 120 and a second section 121 connected to each other, the second section 121 is connected to the column section 11, and the upper surface of the second section 121 is disposed obliquely downward to guide the embedded end 41 into the light path channel 3, and the thickness of the second section 121 is gradually reduced from the end close to the first section 120 toward the end far from the first section 120, and is in smooth transition. The column section 11 includes a third section 110 and a fourth section 111 connected to each other, and the thickness of the fourth section 111 gradually decreases from one end close to the third section 110 to one end far from the third section 110 to abut against the second section 121, so that the optical fiber 4 embedded in the optical path channel 3 between the second section 121 and the fourth section 111 does not bend excessively and can smoothly enter the thermal insulation structure 1.
Preferably, the tilt angle of the second segment 121 is α, and 0< α ≦ 30 °. Under the condition that the first segment 120 is not changed, the larger the inclination angle of the second segment 121 is, the longer the length of the second segment 121 is, the smaller the inclination angle of the second segment 121 is, and the shorter the length of the second segment 121 is, so that the inclination angle of the second segment 121 can be determined according to the actual thickness of the first segment 120, and the optical fiber 4 embedded in the optical path channel 3 can be ensured not to be excessively bent.
Example 2:
the basic contents of the embodiment 2 of the present application are the same as those of the embodiment 1, except that:
referring to fig. 2, the optical path channel 3 is formed by the end surfaces of the pillar section 11 and the rear head section 13 connected to each other, and the embedded end 41 extends along the generatrix direction of the rear head section 13 to be embedded in the optical path channel 3. The optical fiber 4 penetrates into the heat insulation structure 1 from the junction position of the rear head sealing section 13 and the column section 11, and the junction position of the rear head sealing section 13 and the column section 11 is contacted with high-temperature fuel gas when the work of the engine is close to the end, so that the device has the advantages of short exposure time, high reliability and long test time range. However, since the thermal insulation structure 1 is manufactured by first manufacturing the front block section 12, it is more practical that the optical path passage 3 is formed by the end surfaces of the pillar section 11 and the front block section 12 which are connected to each other.
Example 3:
the basic contents of the embodiment 3 of the present application are the same as those of the embodiment 1, except that:
referring to fig. 2, the optical path channel 3 is formed by the end face where the column section 11 and the front head sealing section 12 are connected to each other and the end face where the column section 11 and the rear head sealing section 13 are connected to each other, the embedded end 41 extends along the bus direction of the front head sealing section 12 to be embedded in the optical path channel 3 formed by the column section 11 and the front head sealing section 12, and the embedded end 41 extends along the bus direction of the rear head sealing section 13 to be embedded in the optical path channel 3 formed by the rear head sealing section 13 and the front head sealing section 12. The mode that the front sealing head section 12 and the rear sealing head section 13 are embedded into the heat insulation structure 1 is adopted, the embedding success rate of the optical fibers 4 can be greatly increased, two sections of positions of the propellant grain 2 can be monitored, and monitoring is more comprehensive and efficient.
Example 4:
referring to fig. 3-5, embodiment 4 of the present application provides a method of manufacturing a solid rocket engine case, comprising the steps of:
s1: providing a plurality of optical fibers 4, the optical fibers 4 including a pigtail 40 and an embedded end 41;
s2: the winding core mould 7 is provided with the heat insulation structure 1, a charge space 10 for containing the propellant grain 2 is arranged in the heat insulation structure 1, the heat insulation structure 1 is provided with a light path channel 3 extending along the circumferential direction of the heat insulation structure 1, the light path channel 3 is the occupied space of the optical fiber 4, after the optical fiber 4 enters the light path channel 3, the light path channel 3 is closed, and the optical fiber 4 and the heat insulation structure 1 form an integral structure;
s3: arranging all the optical fibers 4 at intervals along the outer circumferential direction of the front sealing head section 12, extending the leading-out end 40 of each optical fiber 4 out of the heat insulation structure 1, and extending the embedded end 41 into the light path channel 3 and the charge space 10 along the bus direction of the heat insulation structure 1; because the optical fiber 4 is tiny in size, the heat insulation structure 1 is integrally formed with the heat insulation structure 1 after being cured, the optical fiber 4 enters the optical path channel 3 and then seals the optical path channel 3, the whole heat insulation structure 1 is seamless, and the stability and the safety of an engine are not influenced.
S4: winding outside the heat insulation structure 1 to form a winding layer 6;
s5: all the fibres 4 are monitored for viability and a sensor 5 is attached to the embedded end 41 of the viable fibres 4 to monitor the propellant charge 2.
As the diameter of the optical fiber 4 is small (0.25mm), the defects of the heat insulation structure 1 and the damage of the optical path channel 3 can not be caused in the process of introducing the optical fiber 4 into the heat insulation structure 1 of the engine. Due to the particularity of the working environment of the solid rocket engine, the thin optical fiber 4 is difficult to be safely led out from the inside of the engine and external signal collection is realized, while the optical fiber 4 is caused in the manufacturing process of the heat insulation structure 1, the manufacturing process of the heat insulation structure 1 is not influenced, the embedded end 41 of the optical fiber 4 can be successfully led into the heat insulation structure 1, the leading-out end 40 is left outside the heat insulation structure 1, and external signal collection is realized. After the heat insulation structure 1 is subjected to the processes of core mold winding 7 demolding, water pressure test of the heat insulation structure 1, heat insulation polishing before charging and the like, the embedded end 41 of the living optical fiber 4 and the sensor 5 are subjected to field fusion welding, and the sensor 5 is arranged on the inner surface of the heat insulation structure 1 or inside the propellant grain 2 according to requirements, so that the survival rate of the optical fiber 4 can be greatly improved, and the cost is remarkably reduced.
Preferably, the heat insulating structure 1 comprises a column section 11 and a front head sealing section 12 and a rear head sealing section 13 respectively connected to both ends of the column section 11; the light path channel 3 is formed by the end surfaces of the column section 11 and the front sealing head section 12 which are connected with each other;
in S2, the step of mounting the thermal insulation structure 1 on the winding core mold 7 specifically includes the steps of:
s21: preparing a front seal head section and a rear seal head section by adopting a compression molding mode;
s22: a front head seal section 12 and a rear head seal section 13 are fitted to the winding core mold 7 at intervals in the axial direction of the winding core mold 7;
s23: arranging all the optical fibers 4 at intervals along the outer circumferential direction of the front head sealing section 12, extending the leading-out ends 40 of the optical fibers 4 out of the front head sealing section 12, and extending the embedded ends 41 to the end faces of the front head sealing section 12, which are connected with the column section 11, along the bus direction of the front head sealing section 12 and into the powder charging space 10;
s24: paving and pasting a heat insulation segment on the winding core mould 7 between the front head sealing segment 12 and the rear head sealing segment 13, paving and pasting the heat insulation segment from the end surface where the front head sealing segment 12 and the column segment 11 are connected to each other to the rear head sealing segment 13, and connecting the front head sealing segment 12 and the rear head sealing segment 13 to form the column segment 11; the column section 11, the optical fiber 4 and the front sealing head section 12 form an integral structure, and the optical fiber 4 is embedded into the optical path channel 3 to seal the optical path channel 3.
S25: the front head seal section 12, the column section 11 and the rear head seal section 13 together form the insulating structure 1. The heat insulation structure 1 and the optical fiber 4 are integrally formed, and the optical path channel 3 is closed, so that the stability and the safety of the engine are not influenced.
Further, when the light path channel 3 is formed by the end surfaces of the column section 11 and the front head-sealing section 12 connected to each other, the front head-sealing section 12 includes a first section 120 and a second section 121 connected to each other, the second section 121 is connected to the column section 11, and the upper surface of the second section 121 is disposed obliquely downward to guide the embedded end 41 into the light path channel 3. The column section 11 includes a third section 110 and a fourth section 111 connected to each other, and the thickness of the fourth section 111 gradually decreases from one end close to the third section 110 to one end far from the third section 110 to abut against the second section 121, so that the optical fiber 4 embedded in the optical path channel 3 between the second section 121 and the fourth section 111 does not bend excessively and can smoothly enter the thermal insulation structure 1.
The manufacturing method of the solid rocket engine shell in embodiment 4 of the application is as follows:
s21: a front head sealing section 12 and a rear head sealing section 13 are installed on the winding core mould 7, the front head sealing section 12 comprises a first section 120 and a second section 121 which are connected with each other, the second section 121 is connected with the column section 11, and the upper surface of the second section 121 is obliquely arranged downwards;
s22: arranging all the optical fibers 4 at intervals along the outer circumferential direction of the front head sealing section 12, extending the leading-out ends 40 of the optical fibers 4 out of the front head sealing section 12, extending the embedded ends 41 to the second section 121 along the bus direction of the front head sealing section 12, and extending into the powder charging space 10 along with the inclination of the upper surface of the second section 121;
s23: laying a heat insulation segment on the winding core mould 7 between the front head sealing section 12 and the rear head sealing section 13 to form a fourth section 111, wherein the fourth section 111 is abutted with the second section 121 and is integrated with the optical fiber 4;
s24: continuously paving the heat insulation segments to form a third segment 110, connecting the third segment 110 with a fourth segment 111 and a rear head sealing segment 13, and enabling the front head sealing segment 12, the column segment 11 and the rear head sealing segment 13 to jointly form a heat insulation structure 1;
s25: the winding is performed outside the insulating structure 1 to form a winding layer 6.
In step S5, monitoring whether all the optical fibers 4 are alive includes the following steps:
s51: connecting an optical fiber jumper wire at the leading-out end 40 of the optical fiber 4;
s52: connecting a laser pen with an optical fiber jumper to communicate the optical fiber 4;
s53: if the embedded end 41 of the optical fiber 4 is bright, the optical fiber 4 is judged to be alive; otherwise, judging that the optical fiber 4 does not survive;
s54: the above steps are repeated to monitor whether all the optical fibers 4 are alive.
Example 5:
referring to fig. 2, embodiment 5 of the present application provides a solid rocket engine, which includes a heat insulating structure 1, a propellant grain 2, a plurality of optical fibers 4, a plurality of sensors 5, and a winding layer 6, a charge space 10 for accommodating the propellant grain 2 is provided in the heat insulating structure 1, a light path channel 3 extending along the circumferential direction of the heat insulating structure 1 is provided on the heat insulating structure 1, the light path channel 3 is an occupied space of the optical fibers 4 themselves, after the optical fibers 4 enter the light path channel 3, the light path channel 3 is closed, and the optical fibers 4 and the heat insulating structure 1 form an integral structure. The propellant grain 2 is filled in the charging space 10; the winding layer 6 is wound around the thermal insulation structure 1. The optical fibers 4 are arranged at intervals along the outer circumferential direction of the heat insulation structure 1, each optical fiber 4 comprises a leading-out end 40 and an embedded end 41, each leading-out end 40 extends out of the heat insulation structure 1, and each embedded end 41 extends into the light path channel 3 embedded in the bus direction of the heat insulation structure 1 and extends into the propellant powder column 2; because the optical fiber 4 is tiny in size, the heat insulation structure 1 is integrally formed with the heat insulation structure 1 after being cured, the optical fiber 4 enters the optical path channel 3 and then seals the optical path channel 3, the whole heat insulation structure 1 is seamless, and the stability and the safety of an engine are not influenced. The embedded end 41 of the optical fiber 4 is connected with one or more sensors 5, the sensors 5 are embedded in the propellant grain 2, and the sensors 5 can be arranged at the heat insulation interface of the heat insulation structure 1, the lining interface (the adhesive between the propellant grain 2 and the heat insulation structure 1) or the inside of the propellant grain 2 according to different monitoring requirements. The propellant grain 2 can be monitored in situ in real time, the monitoring result is timely and reliable, so that the data of the changes of the surface and the internal strain, the temperature and the like of the propellant grain 2 along with the environmental load can be obtained, and the stability and the safety of the engine can be accurately judged.
The solid rocket engine of embodiment 5 of the present application realizes in-situ monitoring of the interior of the engine by pre-embedding the optical fiber 4 and the sensor 5, and has the following advantages: as the diameter of the optical fiber 4 is small (0.25mm), the defects of the heat insulation structure 1 and the damage of the optical path channel 3 can not be caused in the process of introducing the optical fiber 4 into the heat insulation structure 1 of the engine. And can realize online, real-time, initiative monitoring and control to propellant powder column 2 inside the heat insulating structure 1, find and confirm debonding, propellant powder column 2 internal crack, damaged position and degree of 2 in propellant powder column of the joint interface of 2 in time and heat insulating structure 1, and monitor the expansion of the damaged area, not merely can strengthen the engine state prediction ability effectively, reduce the difficulty of engine detection and fault discrimination, promote engine life-span and reliability, and facilitate the discovery of the early problem of propellant powder column 2, thus take the remedial measure in time, in order to avoid the emergence of the major accident, guarantee the safety and stability of the solid rocket engine.
Example 6:
the embodiment 6 of the application provides a manufacturing method of a solid rocket engine, which comprises the following steps:
s1: providing a plurality of optical fibers 4, the optical fibers 4 including a pigtail 40 and an embedded end 41;
s2: the winding core mould 7 is provided with the heat insulation structure 1, a charge space 10 for containing the propellant grain 2 is arranged in the heat insulation structure 1, the heat insulation structure 1 is provided with a light path channel 3 extending along the circumferential direction of the heat insulation structure 1, the light path channel 3 is the occupied space of the optical fiber 4, after the optical fiber 4 enters the light path channel 3, the light path channel 3 is closed, and the optical fiber 4 and the heat insulation structure 1 form an integral structure;
s3: arranging all the optical fibers 4 at intervals along the outer circumferential direction of the front sealing head section 12, extending the leading-out end 40 of each optical fiber 4 out of the heat insulation structure 1, and extending the embedded end 41 into the light path channel 3 and the charge space 10 along the bus direction of the heat insulation structure 1; the optical fiber 4 is tiny in size, the heat insulation structure 1 is integrally formed with the heat insulation structure 1 after being cured, the optical fiber 4 enters the optical path channel 3 and then seals the optical path channel 3, the whole heat insulation structure 1 is seamless, and the stability and the safety of an engine are not influenced;
s4: winding outside the heat insulation structure 1 to form a winding layer 6;
s5: monitoring whether all the optical fibers 4 are alive or not, and connecting a sensor 5 at the embedded end 41 of the alive optical fibers 4;
s6: removing the winding core mould 7;
s7: the propellant charge 2 is cast in the charge space 10 so that the sensor 5 extends into the propellant charge 2 and monitors the propellant charge 2.
Preferably, the heat insulating structure 1 comprises a column section 11 and a front head sealing section 12 and a rear head sealing section 13 respectively connected to both ends of the column section 11; the light path channel 3 is formed by the end surfaces of the column section 11 and the front sealing head section 12 which are connected with each other;
in S2, the step of mounting the thermal insulation structure 1 on the winding core mold 7 specifically includes the steps of:
s21: preparing a front seal head section and a rear seal head section by adopting a compression molding mode;
s22: a front head seal section 12 and a rear head seal section 13 are fitted to the winding core mold 7 at intervals in the axial direction of the winding core mold 7;
s23: arranging all the optical fibers 4 at intervals along the outer circumferential direction of the front head sealing section 12, extending the leading-out ends 40 of the optical fibers 4 out of the front head sealing section 12, and extending the embedded ends 41 to the end faces of the front head sealing section 12, which are connected with the column section 11, along the bus direction of the front head sealing section 12 and into the powder charging space 10;
s24: paving and pasting a heat insulation segment on the winding core mould 7 between the front head sealing segment 12 and the rear head sealing segment 13, paving and pasting the heat insulation segment from the end surface where the front head sealing segment 12 and the column segment 11 are connected to each other to the rear head sealing segment 13, and connecting the front head sealing segment 12 and the rear head sealing segment 13 to form the column segment 11; the column section 11, the optical fiber 4 and the front sealing head section 12 form an integral structure, and the optical fiber 4 is embedded into the optical path channel 3 to seal the optical path channel 3.
S25: the front head seal section 12, the column section 11 and the rear head seal section 13 together form the insulating structure 1. The heat insulation structure 1 and the optical fiber 4 are integrally formed, and the optical path channel 3 is closed, so that the stability and the safety of the engine are not influenced.
As the diameter of the optical fiber 4 is small (0.25mm), the defects of the heat insulation structure 1 and the damage of the optical path channel 3 can not be caused in the process of introducing the optical fiber 4 into the heat insulation structure 1 of the engine. Moreover, the optical fiber 4 is embedded when the heat insulation structure 1 is manufactured, so that the manufacturing process of the heat insulation structure 1 is not influenced, and the optical fiber 4 can be efficiently embedded. After the heat insulation structure 1 is subjected to the processes of core mold winding 7 demolding, water pressure test of the heat insulation structure 1, heat insulation polishing before charging and the like, the embedded end 41 of the living optical fiber 4 and the sensor 5 are subjected to field fusion welding, and the sensor 5 is arranged on the inner surface of the heat insulation structure 1 or inside the propellant grain 2 according to requirements, so that the survival rate of the optical fiber 4 can be greatly improved, and the cost is remarkably reduced.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A solid rocket engine casing, comprising:
the propellant powder column packaging structure comprises a heat insulation structure (1), wherein a powder charging space (10) for accommodating a propellant powder column (2) is formed in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is formed in the heat insulation structure (1);
a plurality of optical fibers (4), wherein the optical fibers (4) are arranged at intervals along the outer circumferential direction of the heat insulation structure (1), the optical fibers (4) comprise an outgoing end (40) and an embedded end (41), the outgoing end (40) extends out of the heat insulation structure (1), and the embedded end (41) extends along the generatrix direction of the heat insulation structure (1) to be embedded in the light path channel (3) and extend into the powder charging space (10);
a plurality of sensors (5), the sensors (5) being connected to the embedded ends (41) of the optical fibers (4), the sensors (5) being for monitoring the propellant grains (2);
a winding layer (6) wound outside the insulating structure (1).
2. A solid rocket engine casing according to claim 1, wherein said heat insulating structure (1) comprises a column section (11) and a front head section (12) and a rear head section (13) connected to the two ends of said column section (11), respectively; the light path channel (3) is formed by end faces of the column section (11) and the front head sealing section (12) which are connected with each other, and the embedded end (41) extends to be embedded in the light path channel (3) along the bus direction of the front head sealing section (12); and/or, light path passageway (3) by column section (11) with back sealing head section (13) interconnect's terminal surface forms, embedding end (41) are followed the generating line direction of back sealing head section (13) extends to the embedding and locates in light path passageway (3).
3. A solid rocket engine housing as claimed in claim 2, wherein when said light path channel (3) is formed by the end faces of said column section (11) and said front head section (12) being connected to each other, said front head section (12) comprises a first section (120) and a second section (121) being connected to each other, said second section (121) being connected to said column section (11), and the upper surface of said second section (121) being disposed obliquely downward to guide said embedded end (41) into said light path channel (3).
4. A solid rocket engine housing as claimed in claim 3, wherein said column section (11) comprises a third section (110) and a fourth section (111) connected to each other, said fourth section (111) having a thickness gradually decreasing from an end close to said third section (110) towards an end remote from said third section (110) to abut on said second section (121).
5. The solid rocket engine housing according to claim 3, wherein the angle of inclination of said second segment (121) is α, 0< α ≦ 30 °.
6. A manufacturing method of a solid rocket engine shell is characterized by comprising the following steps:
providing a plurality of optical fibers (4), the optical fibers (4) comprising a pigtail end (40) and an embedded end (41);
assembling a heat insulation structure (1) on a winding core mold (7), wherein a charge space (10) for accommodating a propellant grain (2) is arranged in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is arranged on the heat insulation structure (1);
arranging all the optical fibers (4) at intervals along the outer circumferential direction of the heat insulation structure (1), extending the leading-out ends (40) of the optical fibers (4) out of the heat insulation structure (1), and extending the embedded ends (41) into the light path channel (3) and the charge space (10) along the generatrix direction of the heat insulation structure (1);
winding outside the heat insulation structure (1) to form a winding layer (6);
detecting whether all the optical fibers (4) are alive or not, and connecting a sensor (5) at the embedded end (41) of the alive optical fibers (4) to monitor the propellant grains (2).
7. A method of manufacturing a solid rocket engine casing according to claim 6, wherein said insulating structure (1) comprises a column section (11) and a front head seal section (12) and a rear head seal section (13) respectively connected to both ends of said column section (11); the light path channel (3) is formed by the end faces of the column section (11) and the front sealing head section (12) which are connected with each other;
the method for assembling the heat insulation structure (1) on the winding core mould (7) specifically comprises the following steps:
preparing the front sealing head section and the rear sealing head section by adopting a compression molding manner;
the front head sealing section (12) and the rear head sealing section (13) are assembled on the winding core mould (7) at intervals along the axial direction of the winding core mould (7);
arranging all the optical fibers (4) at intervals along the outer circumferential direction of the front head sealing section (12), extending the leading-out ends (40) of the optical fibers (4) out of the front head sealing section (12), and extending the embedded ends (41) into the charge space (10) along the bus direction of the front head sealing section (12);
laying a heat insulation segment on a winding core mould (7) between the front head sealing section (12) and the rear head sealing section (13) to form the column section (11);
the front head section (12), the column section (11) and the rear head section (13) together form the heat insulating structure (1).
8. Method for manufacturing a solid-rocket motor casing according to claim 6, wherein monitoring all the optical fibers (4) for survival comprises the following steps:
connecting an optical fiber jumper at the leading-out end (40) of the optical fiber (4);
connecting a laser pen with the optical fiber jumper to communicate the optical fiber (4);
if the embedded end (41) of the optical fiber (4) is bright, judging that the optical fiber (4) is alive; otherwise, judging that the optical fiber (4) is not alive;
and repeating the steps to monitor whether all the optical fibers (4) are alive or not.
9. A solid rocket engine, comprising:
the propellant powder column packaging structure comprises a heat insulation structure (1), wherein a powder charging space (10) for accommodating a propellant powder column (2) is formed in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is formed in the heat insulation structure (1);
a propellant grain (2) filled in the charge space (10);
a plurality of optical fibers (4), wherein the optical fibers (4) are arranged at intervals along the outer circumferential direction of the heat insulation structure (1), the optical fibers (4) comprise an outgoing end (40) and an embedded end (41), the outgoing end (40) extends out of the heat insulation structure (1), and the embedded end (41) extends along the generatrix direction of the heat insulation structure (1) to be embedded in the light path channel (3) and extend into the propellant grain (2);
a plurality of sensors (5), the sensors (5) being connected to the embedded ends (41) of the optical fibers (4), the sensors (5) being for monitoring the propellant grains (2);
a winding layer (6) wound outside the insulating structure (1).
10. A manufacturing method of a solid rocket engine is characterized by comprising the following steps:
providing a plurality of optical fibers (4), the optical fibers (4) comprising a pigtail end (40) and an embedded end (41);
assembling a heat insulation structure (1) on a winding core mold (7), wherein a charge space (10) for accommodating a propellant grain (2) is arranged in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is arranged on the heat insulation structure (1);
arranging all the optical fibers (4) at intervals along the outer circumferential direction of the heat insulation structure (1), extending the leading-out ends (40) of the optical fibers (4) out of the heat insulation structure (1), and extending the embedded ends (41) into the light path channel (3) and the charge space (10) along the generatrix direction of the heat insulation structure (1);
winding outside the heat insulation structure (1) to form a winding layer (6);
monitoring whether all the optical fibers (4) are alive or not, and connecting a sensor (5) at the embedded end (41) of the alive optical fibers (4);
removing the winding core mould (7);
and spraying a lining layer and pouring the propellant grain (2) in the charging space (10) so as to enable the sensor (5) to extend into the propellant grain (2) and monitor the propellant grain (2).
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