CN205977460U - Rocket engine of anti -backfire - Google Patents
Rocket engine of anti -backfire Download PDFInfo
- Publication number
- CN205977460U CN205977460U CN201620832098.1U CN201620832098U CN205977460U CN 205977460 U CN205977460 U CN 205977460U CN 201620832098 U CN201620832098 U CN 201620832098U CN 205977460 U CN205977460 U CN 205977460U
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- Prior art keywords
- porose disc
- piston
- backfire
- insulated
- heat
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Abstract
The utility model discloses a rocket engine of anti -backfire, it includes gas cylinder, gaseous choke valve, propellant storage box, piston, liquid choke valve, flame arrestor, initial ignition, ignition, combustion chamber and spray tube again, the gas cylinder pass through the intake pipe with propellant storage box's left part is connected, the right part of propellant pass through the feed liquor pipe with flame arrestor one end is connected, flame arrestor's the other end with the combustion chamber intercommunication, the spray tube with the combustion chamber intercommunication, initial ignition set up in on the lateral wall of combustion chamber, again ignition set up in in the combustion chamber, and lie in the combustion chamber with flame arrestor's intercommunication department. The utility model discloses a set up flame arrestor, the service duct of lotion propellant when rocket engine closes, can in time be turn -offed to tempering that can effective control lotion rocket engine, and the consumption that can not produce a large amount of energy can realize flow control on a large scale in addition.
Description
Technical field
This utility model is related to rocket engine, more particularly, to a kind of anti-backfire rocket engine.
Background technology
Pasty propellant is a kind of new non-solid non-liquid propellant, is the special propulsion of a class that chemical rocket advances field
Agent, it is will be uniform to substantial amounts of oxidant, fuel or their mixture with a small amount of gel (or thickening agent, stabilizer)
Stirring is mixed to form has a fixed structure and particular characteristic, and has " toothpaste " shape suspended substance propellant of certain Storage period,
Belong to non-Newtonian fluid, there is the optimal overall characteristic of liquid and solid propellant.Just as solid propellant when it stores, after pressurization
Produce mobility again as liquid propellant, but do not leak, do not explode, safety and reliability.Mastic rocket engine can repeatedly be opened
Shut down and restart, ratio solid engines are easier to control, it is possible to achieve widely thrust is adjusted.Therefore can apply to lead
The electromotor controlling as pose adjustment on bullet and satellite.
The thrust realizing mastic rocket engine is adjusted, and is necessary for controlling the flow of propellant, even flame-out and heavy
New startup.And it is necessary to prevent flame from propagating into propellant tank when flame-out, to prevent propellant tank from exploding.Therefore, cream
Function of preventing back-fire must be had on body rocket engine.
According to published document and patent at present, realizing of function of preventing back-fire is usually to utilize preventing back of pasty propellant
Fiery radial design propellant energy properties pipeline, when pipe radius are less than anti-backfire radius, shortage of heat is with the continuation of flame support
Propagate, thus reaching anti-backfire purpose.Its advantage is not need to design any special device to can be achieved with anti-backfire；And lack
It is also obvious that be usually quite little because of anti-backfire radius, generally only several millimeters, conveying has substantial amounts of energy expenditure to point,
Nor enable large-scale Flow-rate adjustment.
Utility model content
This utility model purpose is to provide a kind of anti-backfire rocket engine, and it is prevented from mastic rocket engine and exists
When quitting work, flame is propagated to propellant tank, improves the safety of mastic rocket engine.
This utility model solves technical problem and adopts the following technical scheme that：A kind of anti-backfire rocket engine, it includes
Gas cylinder, gas throttling valve, propellant tank, piston, liquid choke valve, fireproof tempering device, first igniter, dress of lighting a fire again
Put, combustor and jet pipe；
Described gas cylinder internal memory contains gases at high pressure；
Described piston is slidably disposed in described propellant tank, and described propellant tank is divided into left and right two
Point；Described gas cylinder is connected with the left part of described propellant tank by air inlet pipe, and described air inlet pipe is provided with gas throttling valve；
The right part of described propellant is connected with described fireproof tempering device one end by feed tube, described fireproof tempering device another
One end and described combustion chamber；Described jet pipe and described combustion chamber；
Described igniter first is arranged on the side wall of described combustor, and described igniter again is arranged at described burning
Interior, and it is located at the connectivity part of described combustor and described fireproof tempering device；
Liquid choke valve is provided with described feed tube.
Optionally, described fireproof tempering device is connected with the left end of described combustor；Described jet pipe and the right side of described combustor
End connection.
Optionally, described fireproof tempering device include housing, porose disc seat, porose disc, heat-insulated porose disc, piston bush, flexible member and
Anti-backfire piston；The left end of described housing is connected to feed tube, the right-hand member of described porose disc seat and described combustion chamber；In housing
Being shaped as first shrinking of wall is expanded afterwards, and the expansion end of inner walls and porose disc seat are connected and form the shell body of fireproof tempering device, shell
The inwall of body expansion end is provided with step surface；Porose disc is fixed on the inwall of porose disc seat, and heat-insulated porose disc is arranged on porose disc seat inwall, and
Heat-insulated porose disc one end is connected with porose disc, and the heat-insulated porose disc other end is stuck on the step surface of housing expansion end；Piston bush passes through porose disc
With the center of heat-insulated porose disc, it is connected with porose disc inwall；Anti-backfire piston-top surface is the conical surface, flexible member one end and anti-backfire piston
Bottom connects, and the other end is arranged in piston bush, and anti-backfire piston moves along piston bush；When the non-stress of anti-backfire piston, prevent
The top conical surface of tempering piston is contacted with the original position of housing expansion segment.
Optionally, described porose disc is annular, and ring surface is uniformly distributed multiple through holes；Heat-insulated porose disc is annular, ring surface
On be uniformly distributed multiple through holes, the number of openings on described heat-insulated porose disc is identical with the number of openings on porose disc, heat-insulated porose disc
Through hole is communicated with the through hole of porose disc.
Optionally, described anti-backfire piston base is hollow, and anti-backfire piston base is stretched in flexible member one end.
This utility model has the advantages that：This utility model passes through to arrange fireproof tempering device, being capable of effective control
The tempering of mastic rocket engine, when rocket engine cuts out, can turn off the service duct of pasty propellant in time, will not produce
The consumption of raw substantial amounts of energy, and enable large-scale Flow-rate adjustment.
Brief description
Fig. 1 is the structural representation of anti-backfire rocket engine of the present utility model；
Fig. 2 is the structural representation of fireproof tempering device of the present utility model；
In figure labelling is illustrated as：1- gas cylinder；2- gas throttling valve；3- propellant tank；4- piston；5- liquid choke valve；
6- fireproof tempering device；60- flexible member；61- housing；62- anti-backfire piston；63- screw；64- pad；65- porose disc seat；66-
Porose disc；67- pin；The heat-insulated porose disc of 68-；69- piston bush；70- sealing ring；7- igniter first；8- igniter again；9- fires
Burn room；10- jet pipe；11- pressure transducer；12- controller.
Specific embodiment
With reference to embodiment and accompanying drawing, the technical solution of the utility model is further elaborated.
Embodiment 1
Present embodiments provide a kind of anti-backfire rocket engine, it includes extrusion system, propellant tank, liquid section
Stream valve, fireproof tempering device, again igniter, first igniter, combustor and jet pipe.
In the present embodiment, in described propellant tank, store pasty propellant, described extrusion system can push away described
The pasty propellant entering in agent storage tank extrudes described propellant tank, in the present embodiment, is provided with work in described propellant tank
Plug, described propellant tank is divided into two parts in left and right by described piston, and the right part internal memory of described propellant tank contains mastic
Propellant, described extrusion system includes gas cylinder and gas throttling valve, stores gases at high pressure in described gas cylinder, and described gas cylinder passes through
Air inlet pipe is connected with the left part of described propellant tank, when gas flows into propellant tank in described gas cylinder, gases at high pressure
Piston is promoted to move right, thus pasty propellant is extruded propellant tank.
Preferably, described air inlet pipe is provided with gas throttling valve, described gas throttling valve can control in air inlet pipe
Gas flow rate and flow, such that it is able to realize the control to pasty propellant extruded velocity.
The right part of described propellant tank passes through feed tube and described combustion chamber, or the right side of described propellant tank
Portion is connected to described fireproof tempering device, described fireproof tempering device and described combustion chamber by feed tube, and mastic is advanced
Agent is delivered to described combustor by feed tube, and in burning Indoor Combustion, in the present embodiment, described feed tube and described combustion
Burn room left end connection, described igniter first and again igniter may be contained within described burning interior, and described first
Igniter is arranged on the side wall of described combustor, and igniter is arranged at described combustor and (is prevented with described feed tube again
Back-fire arrangement) connectivity part, the mastic being entered by described feed tube by described igniter again enter described combustion
Burn indoor.
The right-hand member of described combustor is connected with described jet pipe, the gas of the High Temperature High Pressure in described burning is passed through described
Jet pipe sprays, thus booster rocket travels forward.
On described feed tube, liquid choke valve and fireproof tempering device are disposed with along along the flow direction of pasty propellant,
Described liquid choke valve can adjust flow velocity and the flow of described pasty propellant, and described fireproof tempering device is prevented from flame to pushing away
Enter in agent storage tank and propagate.
In the present embodiment, described fireproof tempering device includes housing, porose disc seat, porose disc, heat-insulated porose disc, piston bush, elasticity unit
Part and anti-backfire piston；The left end of described housing is connected to feed tube, the right-hand member of described porose disc seat and described combustion chamber；Shell
Being shaped as first shrinking of internal wall expand afterwards, and one end (right-hand member) of inner walls expansion and porose disc seat pass through screw and be connected to be formed to prevent
The shell body of back-fire arrangement；The inwall of housing expansion end is provided with step surface；Porose disc is threadedly secured on the inwall of porose disc seat,
Heat-insulated porose disc is arranged on porose disc seat inwall, and heat-insulated porose disc one end is passed through pin with porose disc and is connected, and the other end is stuck in housing expansion
On the step surface at end；Away from the step surface of housing expansion end, piston bush passes through the center of porose disc and heat-insulated porose disc to porose disc, by spiral shell
Stricture of vagina is connected with porose disc inwall；Anti-backfire piston-top surface is the conical surface, and flexible member one end is connected with anti-backfire piston base, the other end
It is arranged in piston bush, anti-backfire piston moves along piston bush；When the non-stress of anti-backfire piston, the top cone of anti-backfire piston
Face is contacted with the original position of housing expansion segment, plays a part to intercept the expansion that pasty propellant enters housing.
Described porose disc is annular, and ring surface is uniformly distributed multiple through holes；Preferably, the quantity of described through hole is 45；
Heat-insulated porose disc is annular, and ring surface is uniformly distributed multiple through holes, logical in the number of openings on described heat-insulated porose disc and porose disc
Hole number is identical, and the through hole of heat-insulated porose disc is communicated with the through hole of porose disc.
Described anti-backfire piston base is hollow, and anti-backfire piston base is stretched in flexible member one end, i.e. described elasticity unit
Anti-backfire piston base is stretched in one end of part, and the other end is arranged in piston bush so that anti-backfire piston moves along piston bush.This
In embodiment, described flexible member is spring.
In the present embodiment, for ensureing the sealing connecting between described housing and porose disc seat, described housing and porose disc seat
Joint face is provided with pad it is ensured that good between the two sealing.
When the non-stress of anti-backfire piston, the top conical surface of anti-backfire piston is contacted with the original position of housing expansion segment,
To reach sealing effectiveness.
The operation principle of described anti-backfire rocket engine is：When electromotor needs work, the gas in gas cylinder leads to
Cross air inlet pipe and enter propellant tank so that pasty propellant flows along feed tube, and promote connecing of anti-backfire piston and housing
Contacting surface separates, and so that flexible member is compressed, gap between anti-backfire piston and housing for the pasty propellant is flow through, enters housing
Expansion, then sequentially pass through some through holes entrance combustor on heat-insulated porose disc and porose disc, now igniter starts cream
Body propellant is lighted, and produces combustion gas, and combustion gas accelerates to spray through Laval nozzle, produces thrust, and rocket engine works.
When engine stop works, the pressure in propellant tank reduces, and due to the effect of flexible member elastic force, prevents back
Pathway closure between fiery piston and housing, cut-off propellant tank and combustion chamber, are effectively prevented flame to propellant
Storage tank is propagated it is ensured that the safety of mastic rocket engine.
Heat-insulated porose disc can effectively stop the indoor high temperature of burning to the pasty propellant of porose disc upstream by way of conduction of heat
Transmission；Meanwhile, on porose disc certain length porous channel, the flame of in the hole can be made gradually to radiate with the process propagated,
Until it is flame-out, thus playing anti-backfire effect.
When electromotor works again, its work process with work first similar, however it is necessary that using igniter again
Lighted a fire, that is, when burnout, then igniter low-temperature zone because radiating can stop working, when pasty propellant again
When carrying out combustor, then the high temperature section of igniter can pass through pasty propellant therein and be subject to thermal ignition, realize repeatedly opening
Dynamic.
For controlling the indoor pressure of described burning, described burning interior is provided with pressure transducer, the fire of described side's tempering
Arrow electromotor also includes controller, and described pressure transducer is connected with described controller signals, and the burning being gathered is indoor
Pressure signal transmission to described controller, described controller also signal is connected to described gas throttling valve and liquid choke valve,
To realize the regulation to described gas throttling valve and liquid choke valve, thus the mastic propulsion to the indoor supply of described burning for the adjustment
The amount of agent, such that it is able to efficiently control the pressure of described combustor, and further, it is possible to controls the thrust of described rocket.
The sequencing of above example only for ease of description, does not represent the quality of embodiment.
Finally it should be noted that：Above example only in order to the technical solution of the utility model to be described, is not intended to limit；
Although being described in detail to this utility model with reference to the foregoing embodiments, it will be understood by those within the art that：
It still can be modified to the technical scheme described in foregoing embodiments, or wherein some technical characteristics are carried out etc.
With replacement；And these modifications or replacement, do not make the essence of appropriate technical solution depart from this utility model each embodiment technology
The spirit and scope of scheme.
Claims (1)
1. a kind of anti-backfire rocket engine it is characterised in that include gas cylinder, gas throttling valve, propellant tank, piston,
Liquid choke valve, fireproof tempering device, first igniter, again igniter, combustor and jet pipe；
Described gas cylinder internal memory contains gases at high pressure；
Described piston is slidably disposed in described propellant tank, and described propellant tank is divided into left and right two parts；
Described gas cylinder is connected with the left part of described propellant tank by air inlet pipe, and described air inlet pipe is provided with gas throttling valve；
The right part of described propellant is connected with described fireproof tempering device one end by feed tube, the other end of described fireproof tempering device
With described combustion chamber；Described jet pipe and described combustion chamber；
Described igniter first is arranged on the side wall of described combustor, and described igniter again is arranged at described combustor
Interior, and it is located at the connectivity part of described combustor and described fireproof tempering device；
Liquid choke valve is provided with described feed tube；
Described fireproof tempering device is connected with the left end of described combustor；Described jet pipe is connected with the right-hand member of described combustor；
Described fireproof tempering device includes housing, porose disc seat, porose disc, heat-insulated porose disc, piston bush, flexible member and anti-backfire piston；
The left end of described housing is connected to feed tube, the right-hand member of described porose disc seat and described combustion chamber；Being shaped as of inner walls
First shrink and expand afterwards, the expansion end of inner walls and porose disc seat are connected and form the shell body of fireproof tempering device, housing expansion end
Inwall is provided with step surface；Porose disc is fixed on the inwall of porose disc seat, and heat-insulated porose disc is arranged on porose disc seat inwall, and heat-insulated porose disc one
End is connected with porose disc, and the heat-insulated porose disc other end is stuck on the step surface of housing expansion end；Piston bush passes through porose disc and heat-insulated porose disc
Center, with porose disc inwall be connected；Anti-backfire piston-top surface is the conical surface, and flexible member one end is connected with anti-backfire piston base,
The other end is arranged in piston bush, and anti-backfire piston moves along piston bush；When the non-stress of anti-backfire piston, anti-backfire piston
The top conical surface is contacted with the original position of housing expansion segment；
Described porose disc is annular, and ring surface is uniformly distributed multiple through holes；Heat-insulated porose disc is annular, ring surface is uniformly distributed many
Individual through hole, the number of openings on described heat-insulated porose disc is identical with the number of openings on porose disc, the through hole of heat-insulated porose disc and porose disc
Through hole communicates；Described anti-backfire piston base is hollow, and anti-backfire piston base is stretched in flexible member one end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620832098.1U CN205977460U (en) | 2016-08-02 | 2016-08-02 | Rocket engine of anti -backfire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620832098.1U CN205977460U (en) | 2016-08-02 | 2016-08-02 | Rocket engine of anti -backfire |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205977460U true CN205977460U (en) | 2017-02-22 |
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ID=58029719
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620832098.1U Expired - Fee Related CN205977460U (en) | 2016-08-02 | 2016-08-02 | Rocket engine of anti -backfire |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205977460U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529289A (en) * | 2019-07-31 | 2019-12-03 | 北京天兵科技有限公司 | A kind of anti-backfire nozzle and the liquid-propellant rocket engine with the nozzle |
| CN111486022A (en) * | 2020-04-20 | 2020-08-04 | 西安宸极探索空间科技有限公司 | Anti-backfire device and combustion system |
| CN112696286A (en) * | 2020-12-12 | 2021-04-23 | 南京理工大学 | Gel fuel performance test engine |
-
2016
- 2016-08-02 CN CN201620832098.1U patent/CN205977460U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529289A (en) * | 2019-07-31 | 2019-12-03 | 北京天兵科技有限公司 | A kind of anti-backfire nozzle and the liquid-propellant rocket engine with the nozzle |
| CN110529289B (en) * | 2019-07-31 | 2020-11-06 | 北京天兵科技有限公司 | Anti-backfire nozzle and liquid rocket engine with same |
| CN111486022A (en) * | 2020-04-20 | 2020-08-04 | 西安宸极探索空间科技有限公司 | Anti-backfire device and combustion system |
| CN111486022B (en) * | 2020-04-20 | 2021-07-23 | 西安宸极探索空间科技有限公司 | Anti-backfire device and combustion system |
| CN112696286A (en) * | 2020-12-12 | 2021-04-23 | 南京理工大学 | Gel fuel performance test engine |
| CN112696286B (en) * | 2020-12-12 | 2022-05-20 | 南京理工大学 | Gel fuel performance test engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170222 Termination date: 20170802 |