CN206830330U - A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket - Google Patents
A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket Download PDFInfo
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- CN206830330U CN206830330U CN201720323573.7U CN201720323573U CN206830330U CN 206830330 U CN206830330 U CN 206830330U CN 201720323573 U CN201720323573 U CN 201720323573U CN 206830330 U CN206830330 U CN 206830330U
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Abstract
It the utility model is related to a kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket, it is made up of dividing plate fixed body, dividing plate heat guard and dividing plate jam, dividing plate fixed body uses 2A12 high-strength aluminum alloy materials, and the both sides compression molding of dividing plate fixed body has dividing plate heat guard；Dividing plate heat guard uses high silica fiber/phenolic resin pressing, and integrated machine adds to design point after dividing plate heat guard and dividing plate fixed body integral die shaping, and dividing plate heat guard and dividing plate fixed body interphase offer fuel gas hole with opening position；Dividing plate jam uses 2A12 materials, and dividing plate jam is bonded in the dividing plate heat guard of transmitting engine side, and bonding dividing plate jam is in transmitting engine side coating big 703 glued membrane in one layer of south.Melt film formula dividing plate of the present utility model is applied to medium and small engine；Cost is cheap, simple in construction；Evening ejecta departure time, particle diameter are small, and to Types of Medicine without particular/special requirement.
Description
Technical field
A kind of dividing plate of multiple-pulse solid propellant rocket is the utility model is related to, more particularly to one kind is applied to multiple-pulse
The melt film formula dividing plate of solid propellant rocket.
Background technology
Ignition operation of in general solid propellant rocket is until burning terminates, as using one-level solid engines
Air-air or interceptor missile, usual only 1/2 or 1/3 operating within range before guided missile of its engine, after flight integrated range
1/2 or even 2/3, guided missile is unpowered flight, and guided missile necessarily slows down quickly during unpowered flight, so that difficult in the end of trajectory
It is larger motor-driven to carry out again.If the form separated using multi-stage engine, the complicated journey of missile armament is undoubtedly increased again
Degree, reduces reliability.And pulse solid rocket engine can realize multiple igniting, reasonable distribution simultaneously controls each section of thrust
Size, duration and time interval, the shortcomings that solid engines energy-controllable difference can be significantly improved, it is greatly enhanced guided missile
The performance of armament systems.
Pulse solid rocket engine is to realize light a fire, burn respectively using isolating device, so as to realize pulsed operation.Every
There are two kinds from device typical structure：Compartment-type and interlayer type.Combustion chamber is divided into by compartment-type isolating device by separation between level
Multiple independent combustion chamber nacelles, separation should heat-insulated load again, according to the structure type of separation can be divided into injection bar type every
Cabin, metal film chip separation, nonmetallic materials formula separation.Interlayer type isolating device is in structure using interlayer each pulse powder column
Isolate axially or radially, each pulse powder column is lighted a fire respectively, and interlayer mainly serves fire-retardant and heat-insulated, it is not necessary to load, every
Laminar isolating device is divided into axial interlayer type and radial direction interlayer type.
" spray wands " formula separation design principle is to make separation matrix with the infusibility metal material such as chrome-molybdenum steel, above with same
Heart circle best-fit mode, which drills, is used as injection, the step-like spray that spray-hole is made with the fibre reinforced plastics of lighter in weight and resistance to ablation
Rod blocking is penetrated, for the sake of sealing, fills a small "O" ring in each spray wands, big one towards first of spray wands size
Level pulse powder column combustion chamber.So, in first order pulse powder column ignition operation, the spray-hole on dividing plate is by the platform in spray wands
Rank is blocked, so as not to mutually gas blowby and second level pulse powder column is separated, and the pressure of first order pulse is effectively born, when second
During level pulse powder column ignition operation, the pressure from second level pulse powder column combustion chamber easily blows the spray wands on dividing plate
Go out, open partition board hole, and the injection spile being blown is discharged through first-stage burning room from jet pipe together in company with combustion gas stream.This
Kind compartment structure is simple and sealing reliability is high.
Metal film chip separation component includes support member and metallic membrane.Domestic metallic membrane separation mainly by metal or
Person's nonmetallic materials are sealed as support member in the opposite side of support member using the metallic membrane for adhering to heat insulation layer.When
During one pulsed operation, the load that metallic membrane bears a pulse-combustion chamber pressure does not rupture and effectively seals a gas-burning pulse；Two
During pulsed operation, under relatively low pressure, rupture of diaphragm ensures two pulse normal works, and fragment is not produced after rupture of diaphragm,
In order to avoid the structures such as jet pipe are damaged.
Nonmetallic materials separation uses a kind of glass ceramics cut, ground and drilled.The resistance to compression of material
Intensity is much larger than tensile strength, is processed into convex-shaped during use, convex surface facing first-stage burning room, it is born first order pulse
High pressure when powder column burns.When second level powder column burns, separation concave surface tension and it is more broken, fragment is with combustion gas stream from jet pipe
Discharge.There is certain randomness because ceramic material is broken, to prevent large scale fragment, indentation can be processed in convex side,
Crushed with guide diaphragm along indentation, control chip size and cut shape.
Axial interlayer is primarily adapted for use in the dipulse engine of minor diameter（φ200）, the shape of most axial interlayer
For " cap " shape.Axial interlayer have it is simple in construction, be easily worked, passive light weight, but two pulse Types of Medicine are limited, it is necessary to for end
Face burning Types of Medicine, are used as the support of interlayer.
Radial direction interlayer is applied to larger-diameter dipulse engine, and radial direction interlayer has that principle is simple, II pulse Types of Medicine
Substantially the advantages that unrestricted, passive light weight.
Moment of the spray wands in the second pulsed operation on " spray wands " formula separation all will blow out disengaging simultaneously and beat
It is relatively difficult to open the spray-hole on dividing plate, thus can cause to push away the fluctuation of force-time curve；In addition, when the second pulse work
When making, fuel gas flow has certain capacity loss by small spray-hole on dividing plate（Because these orifice sizes far smaller than spray
Pipe larynx footpath size, make to be formed to be jammed during airflow passes aperture to throttle and cause）.
It is metal film chip compartment structure quality weight, adiabatic difficult, it is only applicable to that mass ratio is less demanding, the working time is not grown
Dipulse engine.
The shortcomings of nonmetallic materials compartment structure quality is heavy, pressure-bearing and opening pressure ratio are small, especially sensitive to material.
II pulse Types of Medicine of axial interlayer are limited, it is necessary to are cigarette burning Types of Medicine, are used as the support of interlayer；Radially every
Layer has that powder charge, ignition process are complicated, and the II pulsed operation interlayer thing that flies out is more.
Above-mentioned several isolating devices are analyzed, in general function realization, physical dimension, security and cost requirement side
Face is remained in certain defect.
The content of the invention
The technical problems to be solved in the utility model is to provide a kind of melt film suitable for multiple-pulse solid propellant rocket
Formula dividing plate, to solve the problems, such as the isolation being applied on multiple-pulse solid propellant rocket.
For technical problem existing for solution, the technical solution adopted in the utility model is：One kind is applied to multiple-pulse solid
The melt film formula dividing plate of rocket engine, is made up of dividing plate fixed body, dividing plate heat guard and dividing plate jam, described dividing plate fixed body
Using 2A12 high-strength aluminum alloy materials, the both sides compression molding of dividing plate fixed body has dividing plate heat guard；Described dividing plate heat guard is adopted
With high silica fiber/phenolic resin pressing, integrated machine adds to after dividing plate heat guard and dividing plate fixed body integral die shaping
Design point, dividing plate heat guard and dividing plate fixed body interphase offer fuel gas hole with opening position, are burnt for aircraft engines
Combustion gas in room is flowed through by fuel gas hole to be sprayed by jet pipe after transmitting engine chamber；Described dividing plate jam uses 2A12 materials
Material, dividing plate jam are bonded in the dividing plate heat guard of transmitting engine side, for the fuel gas hole of enclosed baffle heat guard, bonding
Good dividing plate jam is in transmitting engine side coating big 703 glued membrane in one layer of south.
The present invention's bears the first pulse combustor, that is, launching the sustained load of engine pressure will not destroy, and have
Effect the first gas-burning pulse of sealing；, will be rapid under compared with low pressure load when second pulse combustor, i.e. aircraft engines are lighted a fire
Destroy so that the second gas-burning pulse passes through；Dividing plate after destruction does not influence engine work, does not destroy engine jet pipe etc.
Structure, do not injure shooter；There is good work reappearance；Cost is cheap.
Beneficial effect
The present invention relates to application of the isolating device on solid propellant rocket, is to utilize isolating device in particular
If the combustion chamber of solid propellant rocket is divided into stem portion, repeatedly shut down and start, reasonable distribution thrust and each pulse
Interval time, the optimum control of missile flight trajectory and the Optimal Management of engine power are realized, improve all kinds of tactics comprehensively and lead
The performance of bullet system.Compared with other dividing plates, it the advantage is that：
1) it is simple in construction
Melt film formula dividing plate is made up of dividing plate fixed body, dividing plate heat guard and dividing plate jam.And spray wands dividing plate is by with holes
Jet lid and the more spray wands composition being inserted in hole, structure are more complicated；
2) cost is cheap, lighter weight
The structural material of melt film formula dividing plate is 2A12 materials, high silica fiber/phenolic resin moulding material, cost is cheap,
Lighter weight.Ceramic separator material not only quality weight, and more sensitive to material in processing is made；
3) evening ejecta departure time, particle diameter are small
In secondary work, dividing plate works progressively to melt from jet pipe with two stage motors to fly the engine of melt film formula dividing plate
Go out, and the ejecta particle diameter of molten state is smaller, does not destroy engine jet pipe.Ceramic separator starts in the work of two stage motors
When, because ceramic separator is opened, just have ejecta and fly out, and due to attribute of ceramic material itself, ejecta particle diameter is larger, holds
Destructible engine jet pipe；
4) to Types of Medicine without particular/special requirement
The engine of melt film formula dividing plate to the Types of Medicine of every stage motor without particular/special requirement, and requirement of the flexible barrier to Types of Medicine
Higher, it is end-burning grain that such as axial interlayer, which needs two level powder column, to be supported to interlayer.
To sum up, the present invention and prior art contrast are as shown in table 1：
The diaphragm structure form of table 1 and feature
| Melt film formula dividing plate | Ceramic separator | Spray wands dividing plate | Flexible barrier | |
| It is applicable caliber | It is middle or small | It is big or middle | In | It is small |
| Cost | It is low | It is high | It is low | In |
| Mechanism complexity | Simply | It is complicated | Simply | It is complicated |
| Working time | In | It is long | In | It is short |
| The ejecta departure time | Evening | It is early | It is early | Evening |
| Ejecta particle diameter | It is small | Greatly | Greatly | It is small |
| It is other | -- | -- | -- | There is particular/special requirement to Types of Medicine |
As can be seen from Table 1, melt film formula dividing plate compares other dividing plates, suitable for medium and small engine；Cost is cheap, knot
Structure is simple；Evening ejecta departure time, particle diameter are small, and to Types of Medicine without particular/special requirement.
Brief description of the drawings
Fig. 1 is melt film formula diaphragm structure schematic diagram, in figure, including dividing plate fixed body 1, dividing plate heat guard 2, dividing plate jam 3；
Fig. 2 is melt film formula diaphragm structure left view；
Fig. 3 is melt film formula diaphragm structure right view；
Fig. 4 is XL-1 monoblock type Double pulse solid rocket motor schematic diagrames, in figure, including aircraft engines igniter
4th, aircraft engines combustion chamber 5, baffle assembly 6, transmitting engine ignitor 7, transmitting engine chamber 8；
Fig. 5 is 13.72MPa forward direction pressure-bearing fire trial test curves；
Fig. 6 is 12.61MPa forward direction pressure-bearing fire trial test curves；
Fig. 7 is 0.5435MPa reverse opening fire trial test curves；
Fig. 8 is 0.5879MPa reverse opening fire trial test curves；
Fig. 9 is two-stage engine test curve.
Embodiment
The utility model is described further with reference to the accompanying drawings and examples.
As shown in figure 4, XL-1 monoblock types Double pulse solid rocket motor is sent out by aircraft engines igniter 4, flight
Motivation combustion chamber 5, baffle assembly 6, launch engine ignitor 7, transmitting engine chamber 8, jet pipe and directly under part group
Into.
As Figure 1-3, baffle assembly 6 uses melt film formula dividing plate, is blocked up by dividing plate fixed body 1, dividing plate heat guard 2 and dividing plate
Piece 3 forms, and dividing plate fixed body 1 uses 2A12 high-strength aluminum alloy materials, and dividing plate heat guard adopts 2 and uses high silica fiber/phenolic resin
Pressing, integrated machine adds to design point, dividing plate heat guard 2 and the interphase of dividing plate fixed body 1 after the two integral die shaping
5 fuel gas holes of φ 8 are offered with opening position.Dividing plate jam 3 uses 2A12 materials, Nian Jie with dividing plate using epoxy adhesive, Gu
Launch engine side after change and coat one layer of big 703 glued membrane in about 0.5mm south.
The melt film formula dividing plate prepared is threadedly secured to transmitting motor body side, using seal with O ring, melt film
Formula dividing plate is divided into two independent spaces by engine is launched with aircraft engines.
The aircraft engines and transmitting engine two-stage engine calls of XL-1 monoblock type Double pulse solid rocket motors
Separated ignition can be realized, therefore when launching engine ignition work, dividing plate fixed body 1+ dividing plates heat guard 2 is blocked up as dividing plate
The supporting construction of piece 3, dividing plate jam 3 is coordinated to bear to launch engine side operating pressure jointly, dividing plate jam 3 is in transmitting engine
Southern big 703 glued membrane of side bears combustion gas ablation while sealing function is played, and prevents dividing plate jam 3 in transmitting engine
Melted during work, so that aircraft engines powder charge is in an independent closed space, the space is not by transmitting engine
The influence of high-temperature high-pressure fuel gas during work.
When transmitting end of burning, after postponing the regular hour, aircraft engines ignition operation, dividing plate jam 3 becomes
Shape, blast tube are opened, and aircraft engines combustion gas is after 5 fuel gas holes of φ 8 of dividing plate flow through transmitting engine chamber by jet pipe
Spray, during which melt film formula dividing plate progressively melts with aircraft engines work, and ensures to form the gross area leading to more than jet pipe larynx face
Road, prevent engine interior from forming secondary larynx footpath, influence engine structural integrity and technical performance index.
The present invention has already passed through mini-test and more component parts for assembly of a machine engines ground heat runs experiment examination, melt film formula dividing plate are positive
Bearing capacity and reverse opening performance fully meet XL-1 monoblock type Double pulse solid rocket motor structural performance requirements.
1) positive pressure-bearing fire trial
Using heavy wall exerciser carry out dividing plate forward direction pressure-bearing fire trial, transmitting motor charge, jet pipe, igniter and
Dividing plate state of the art is performed by design point, absorbent cotton is set in dividing plate aircraft engines side, to check for combustion gas
Leak case.Experiment actual measurement pressure curve is as shown in Figure 5 and Figure 6.
Shown according to test data, two component parts for assembly of a machine maximum functional pressure are respectively 13.72MPa, 12.61MPa.Decomposed after experiment
Check, absorbent cotton keeps state before experiment, shows no gas leakage.Dividing plate jam bonding glue-line all destroys, big 703 glued membrane in south
Intact, result of the test shows that dividing plate disclosure satisfy that pressure-bearing, Seal Design requirement.
2) reverse opening fire trial
After positive pressure-bearing fire trial, reverse opening fire trial is carried out using igniter pad in aircraft engines side,
Pressure sensor all the way is respectively set in transmitting engine, aircraft engines both sides, adopted with launching engine side pressure sensor
The side pressure sensor of the aircraft engines one actual measurement pressure that collection obtains pressure data a moment opens pressure as dividing plate jam.Due to
There is certain time lag in pressure transmission, therefore dividing plate jam opening pressure should be slightly below the above results.Measured curve such as Fig. 7 and figure
Shown in 8.Shown according to test data, it is respectively 0.5435MPa, 0.5879MPa that two component parts for assembly of a machine dividing plate jams, which open pressure, reappearance
Well.The hole of dividing plate 5 corresponds to jam and opens 3 holes, and aisle spare is more than jet pipe larynx face, meets design requirement.
3) two stage motor joint-trials are tested
Melt film formula dividing plate successively carries out heavy wall steel exerciser, heavy wall aluminium exerciser, just after mini-test is fully verified
Formula state engine 15 sends out fire trial, and maximum functional pressure scope is 12.8027MPa~13.6337MPa, and dividing plate works
Normally.Two-stage engine test curve is as shown in figure 9, from Fig. 9 two-stage engine test curves, melt film formula dividing plate forward direction is held
Pressure energy power and reverse opening performance fully meet XL-1 monoblock type Double pulse solid rocket motor structural performance requirements.
The melt film formula dividing plate of the present invention is made up of dividing plate fixed body, dividing plate heat guard and dividing plate jam, and material is respectively
2A12 materials, high silica fiber/phenolic resin moulding material.If diaphragm structure is constant, only changes dividing plate fixed body 1 or dividing plate is exhausted
The material of hot body 2 or dividing plate jam 3, then it is considered as the design for change of the present invention.
The melt film formula dividing plate further genralrlization that the present invention introduces, double/multiple-pulse Solid Rocket Motor Technology can be made just
Take and be used widely on formula antitank missile, portable ground-to-air missile or even air-to-air missile.
Claims (1)
- A kind of 1. melt film formula dividing plate suitable for multiple-pulse solid propellant rocket, by dividing plate fixed body (1), dividing plate heat guard (2) and dividing plate jam (3) forms, it is characterised in that：Described dividing plate fixed body (1) uses 2A12 high-strength aluminum alloy materials, and dividing plate fixed body (1) both sides compression molding has dividing plate Heat guard (2)；Described dividing plate heat guard (2) uses high silica fiber/phenolic resin pressing, and dividing plate heat guard (2) and dividing plate are consolidated Integrated machine adds to design point after determining body (1) integral die shaping, and dividing plate heat guard (2) and dividing plate fixed body (1) interphase are same Opening position offers fuel gas hole；Described dividing plate jam (3) uses 2A12 materials, and dividing plate jam (3) is bonded in the dividing plate heat guard of transmitting engine side (2) on, for the fuel gas hole of enclosed baffle heat guard (2), bonding dividing plate jam (3) is in transmitting engine side coating one Big 703 glued membrane in layer south.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720323573.7U CN206830330U (en) | 2017-03-30 | 2017-03-30 | A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket |
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|---|---|---|---|
| CN201720323573.7U CN206830330U (en) | 2017-03-30 | 2017-03-30 | A kind of melt film formula dividing plate suitable for multiple-pulse solid propellant rocket |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111036875A (en) * | 2019-12-30 | 2020-04-21 | 珠海凯利得新材料有限公司 | Solid rocket engine blanking cover and preparation method thereof |
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2017
- 2017-03-30 CN CN201720323573.7U patent/CN206830330U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111036875A (en) * | 2019-12-30 | 2020-04-21 | 珠海凯利得新材料有限公司 | Solid rocket engine blanking cover and preparation method thereof |
| CN111036875B (en) * | 2019-12-30 | 2021-04-27 | 珠海凯利得新材料有限公司 | Solid rocket engine blanking cover and preparation method thereof |
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