CN107165739A - Solid-liquid rocket circular seam type plug nozzle - Google Patents
Solid-liquid rocket circular seam type plug nozzle Download PDFInfo
- Publication number
- CN107165739A CN107165739A CN201710616678.6A CN201710616678A CN107165739A CN 107165739 A CN107165739 A CN 107165739A CN 201710616678 A CN201710616678 A CN 201710616678A CN 107165739 A CN107165739 A CN 107165739A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- solid
- ring
- laryngeal mask
- liquid rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
Abstract
The invention discloses a kind of solid-liquid rocket circular seam type plug nozzle, including ring laryngeal mask, jet pipe pressing plate, jet pipe housing, plug cone and heat-insulating shield；The ring laryngeal mask is arranged on the port of export of the jet pipe housing by the jet pipe pressing plate；Boss is provided with by floor in the jet pipe housing；The plug cone is suspended in the throat of the ring laryngeal mask and is connected with the boss；The throat of the outer peripheral face and the ring laryngeal mask of the plug cone cooperatively forms converging portion and expansion segment；The heat-insulating shield is arranged on the arrival end of the jet pipe housing, and the heat-insulating shield is provided with the groove connected with the floor.High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enter via the arrival end of jet pipe housing, and combustion gas is ramped up in converging portion, are reached in the throat of ring laryngeal mask and flow into expansion segment after velocity of sound and continue to accelerate to supersonic speed.Suitable for the solid-liquid rocket of different operating height.
Description
Technical field
The present invention relates to rocket engine field, more particularly to a kind of solid-liquid rocket circular seam type plug nozzle.
Background technology
Jet pipe, as the part of rocket engine, is to influence a key factor of engine performance.
The jet pipe of rocket engine is generally La Faer jet pipes, for the high-temperature high-pressure fuel gas for producing Indoor Combustion of burning
Conversion of heat into kinetic energy.Acceleration constantly is expanded when high-temperature high-pressure fuel gas flow through jet pipe, is finally arranged with high speed from nozzle exit plane
Go out, produce thrust.The jet pipe of existing solid or liquid-propellant rocket engine is generally bell nozzle.
Traditional bell nozzle, because its divergence ratio does not adapt to the change of environmental pressure, in the distribution process of rocket,
Expansion or deficient expansion issues occurred, making the efficiency of jet pipe reduces.Compared with traditional bell nozzle, plug nozzle has certainly
Dynamic height compensation characteristic, can keep higher nozzle efficiency in larger working height range, it is adaptable to which bigger work is high
Spend scope.By rational design and optimization, compared with traditional bell nozzle, the more compact structure of plug nozzle, size is more
Small, weight is lighter.The structure and form of existing plug nozzle are not accounted for all just for solid or liquid-propellant rocket engine
Applicable cases on solid-liquid rocket, are not suitable for solid-liquid rocket.
The content of the invention
It is an object of the invention to provide a kind of solid-liquid rocket circular seam type plug nozzle, to solve in the prior art
The structure and form of the existing plug nozzle existed are not accounted in solid-liquid all just for solid or liquid-propellant rocket engine
Applicable cases on rocket engine, are not suitable for the technical problem of solid-liquid rocket.
The solid-liquid rocket circular seam type plug nozzle that the present invention is provided, including ring laryngeal mask, jet pipe pressing plate, jet pipe shell
Body, plug cone and heat-insulating shield；
The ring laryngeal mask is arranged on the port of export of the jet pipe housing by the jet pipe pressing plate；
Boss is provided with by floor in the jet pipe housing；
The plug cone is suspended in the throat of the ring laryngeal mask and is connected with the boss；
The throat of the outer peripheral face and the ring laryngeal mask of the plug cone cooperatively forms converging portion and expansion segment；
The heat-insulating shield is arranged on the arrival end of the jet pipe housing, and the heat-insulating shield is provided with the floor and connected
Groove.
Further, the throat of the ring laryngeal mask includes the hemispherical-shaped aperture that is sequentially connected and through hole, the plug cone include according to
The arc section and conical section of secondary connection, the end face of the arc section are connected with the boss, the outer peripheral face of the arc section and institute
State hemispherical-shaped aperture to be engaged to form converging portion, the conical section stretches out the through hole of the ring laryngeal mask, the outer peripheral face of the conical section
It is engaged to form expansion segment with the through hole.
Further, the end face of the arc section of the plug cone is provided with groove, and the end face of the arc section of the plug cone passes through
The groove is set on the boss and connected as one by bolt with the boss.
Further, it is provided with the boss in bolt hole, the groove and is provided with screwed hole, the bolt passes through described
Bolt hole is connected with the screwed hole.
Further, the heat-insulating shield is to be detachably connected with the jet pipe housing.
Further, the jet pipe pressing plate is to be detachably connected with the jet pipe housing.
Further, the plug cone of stating is made up of high temperature ablation resistant material.
Further, the ring laryngeal mask is made up of high temperature ablation resistant material.
Further, sealing ring is installed between the port of export of the ring laryngeal mask and the jet pipe housing.
Further, the floor is structure as a whole with the boss.
The solid-liquid rocket circular seam type plug nozzle that the present invention is provided, has the following advantages that：
High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enter via the arrival end of jet pipe housing, and combustion gas is being received
Hold back section to ramp up, reached in the throat of ring laryngeal mask and expansion segment is flowed into after velocity of sound and continue to accelerate to supersonic speed.
1st, suitable for the solid-liquid rocket of different operating height.
2nd, compact conformation, size is smaller, it is adaptable to the ground experiment of solid-liquid rocket.
3rd,, can be in very big working height range with automatic height compensation characteristic compared with traditional bell nozzle
Higher nozzle efficiency is kept, the wider solid-liquid rocket of working height range is particularly suitable for use in.
4th, nozzle entry plane can play a part of flow-disturbing, be conducive to the blending of combustion gas, improve solid-liquid rocket
Efficiency of combustion, improves engine performance.
5th, the actual divergence ratio of jet pipe can change with the change of engine chamber pressure, it is adaptable to the solid-liquid with change propulsive characteristic
Rocket engine.
Brief description of the drawings
, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it should be apparent that, in describing below
Accompanying drawing is some embodiments of the present invention, for those of ordinary skill in the art, before creative work is not paid
Put, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation for the solid-liquid rocket circular seam type plug nozzle that the embodiment of the present invention one is provided；
Fig. 2 is Fig. 1 A-A sectional views；
Fig. 3 is the structural representation for the jet pipe housing that the present embodiment one is provided；
Fig. 4 is Fig. 3 B-B sectional views；
Fig. 5 is the structural representation for the ring laryngeal mask that the present embodiment one is provided；
Fig. 6 is the structural representation for the plug cone that the present embodiment one is provided；
Fig. 7 is the structural representation for the jet pipe pressing plate that the present embodiment one is provided；
Fig. 8 is Fig. 7 C-C sectional views；
Fig. 9 is the structural representation for the heat-insulating shield that the present embodiment one is provided；
Figure 10 is Fig. 9 D-D sectional views.
Reference：1- ring laryngeal masks；2- jet pipe pressing plates；3- jet pipe housings；4- plug cones；5- heat-insulating shields；6- floors；7- is convex
Platform；8- converging portions；9- expansion segments；10- grooves；11- hemispherical-shaped apertures；12- through holes；41- arc sections；42- conical sections；411- ends
Face；412- grooves；13- bolts；31- steps one；51- counter sinks；413- screwed holes；14- sunk screws；21- unthreaded holes；32- platforms
Rank two；33- steps three；15- sealing rings；71- bolt holes；16- grooves.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than indicate or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that indicating or implying relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood as the case may be
Concrete meaning in the present invention.
Embodiment one：
Fig. 1 is the structural representation for the solid-liquid rocket circular seam type plug nozzle that the embodiment of the present invention one is provided；Fig. 2
For Fig. 1 A-A sectional views；Fig. 3 is the structural representation for the jet pipe housing that the present embodiment one is provided；Fig. 4 is Fig. 3 B-B section views
Figure；Fig. 5 is the structural representation for the ring laryngeal mask that the present embodiment one is provided；Fig. 6 is that the structure for the plug cone that the present embodiment one is provided is shown
It is intended to；Fig. 7 is the structural representation for the jet pipe pressing plate that the present embodiment one is provided；Fig. 8 is Fig. 7 C-C sectional views；Fig. 9 is this reality
The structural representation of the heat-insulating shield of the offer of example one is provided；Figure 10 is Fig. 9 D-D sectional views；As shown in Fig. 1-Figure 10, the present invention is provided
Solid-liquid rocket circular seam type plug nozzle, including ring laryngeal mask 1, jet pipe pressing plate 2, jet pipe housing 3, plug cone 4 and heat-insulating shield
5；
The ring laryngeal mask 1 is arranged on the port of export of the jet pipe housing 3 by the jet pipe pressing plate 2；
Boss 7 is provided with by floor 6 in the jet pipe housing 3；
The plug cone 4 is suspended in the throat of the ring laryngeal mask 1 and is connected with the boss 7；
The throat of the outer peripheral face and the ring laryngeal mask 1 of the plug cone 4 cooperatively forms converging portion 8 and expansion segment 9；
The heat-insulating shield 5 is arranged on the arrival end of the jet pipe housing 3, and the heat-insulating shield 5 is provided with phase with the floor 6
The groove 10 of insertion.
Preferably, the throat of the ring laryngeal mask 1 includes hemispherical-shaped aperture 11 and the through hole 12 being sequentially connected, and the plug cone 4 is wrapped
The arc section 41 and conical section 42 being sequentially connected are included, the end face 411 of the arc section 41 is connected with the boss 7, the circular arc
The outer peripheral face of section 41 is engaged to form converging portion 8 with the hemispherical-shaped aperture 11, and the conical section 42 stretches out the through hole 12, described
The outer peripheral face of conical section 42 is engaged to form expansion segment 9 with the through hole 12.
Preferably, the end face 411 of the arc section 41 of the plug cone 4 is provided with groove 412, the arc section 41 of the plug cone 4
End face 411 be set on the boss 7 and connected as one by bolt 13 with the boss 7 by the groove 412.
Groove 412 coordinates with boss 7 for gap, and groove 412, which is located on plug cone 4, can play reduction plug 4 material requesteds of cone, section
The effect of cost-saving.
Preferably, it is provided with the boss 7 in bolt hole 71, the groove 412 and is provided with screwed hole 413, the bolt
13 are connected through the bolt hole 71 with the screwed hole 413 in the groove 412.
Preferably, the heat-insulating shield 5 is with the jet pipe housing 3 to be detachably connected, and the arrival end of jet pipe housing 3 is provided with use
In the step 1 for installing the heat-insulating shield 5.
Heat-insulating shield 5 is provided with counter sink 51, and jet pipe housing 3 is provided with the screwed hole 413 being correspondingly arranged with counter sink 51, sinks
Head screw 14 is threadedly coupled through the counter sink 51 on heat-insulating shield 5 with the screwed hole 413 on jet pipe housing 3.
Counter sink 51 on heat-insulating shield 5 is that the screwed hole 413 on four, jet pipe housing 3 is four.
Four counter sinks 51 on heat-insulating shield 5 are located on heat-insulating shield 5 by center of circle ring of the axis of heat-insulating shield 5.
It should be noted that the counter sink 51 on heat-insulating shield 5 is the position of correspondence counter sink 51 on four, jet pipe housing 3
The screwed hole 413 being provided with is correspondence counter sink on four counter sinks 51 and jet pipe housing 3 being only intended on explanation, heat-insulating shield 5
The screwed hole 413 that 51 position is provided with can also be set to other quantity, just not repeat one by one herein.
Heat-insulating shield 5 is used to protect floor 6 not by high-temperature fuel gas ablation, prevents from causing structural damage.
Preferably, the thickness of heat-insulating shield 5 is 10mm, meets thermal protection requirement.
It is only intended to it should be noted that the thickness of heat-insulating shield 5 is 10mm for example, heat-insulating shield 5 can also use other
Thickness, is not just repeated one by one herein.
Preferably, heat-insulating shield 5 is made up of high silica.
Preferably, the jet pipe pressing plate 2 is to be detachably connected with the jet pipe housing 3.
The position of unthreaded hole 21 that jet pipe pressing plate 2 is provided with unthreaded hole 21, jet pipe housing 3 on correspondence jet pipe pressing plate 2 offers spiral shell
Pit 413, bolt 13 passes through screwed hole 413 of the unthreaded hole 21 with being correspondingly arranged on jet pipe housing 3 on the jet pipe pressing plate 2 to connect
Connect.
Unthreaded hole 21 on jet pipe pressing plate 2 is that the position of the unthreaded hole 21 on correspondence jet pipe pressing plate 2 on eight, jet pipe housing 3 is opened
Provided with eight screwed holes 413.
Eight unthreaded holes 21 on jet pipe pressing plate 2 are arranged on jet pipe pressing plate 2 by center of circle annular of the axis of jet pipe pressing plate 2.
It should be noted that unthreaded hole 21 on jet pipe pressing plate 2 is eight, on jet pipe housing 3 on correspondence jet pipe pressing plate 2 eight
The position of individual unthreaded hole 21 offers the unthreaded hole 21 and jet pipe housing 3 that eight screwed holes 413 are only intended on explanation, jet pipe pressing plate 2
The screwed hole 413 that the position of upper correspondence unthreaded hole 21 is opened up can also be set to other quantity, just not repeat one by one herein.
Preferably, the port of export of the jet pipe housing 3 is provided with the step 2 32 being engaged with the ring laryngeal mask 1, step two
32 coordinate with ring laryngeal mask 1 for gap, and jet pipe pressing plate 2 is provided with the step 3 33 coordinated with ring laryngeal mask 1, step 3 33 and ring laryngeal mask
Coordinate at 1 cooperation for gap, facilitate the positioning of jet pipe pressing plate 2.
Preferably, the heat-insulating shield 5 is set to four with the groove 10 connected on the floor 6.
It is only intended to illustrate it should be noted that heat-insulating shield 5 is set to four with the groove 10 connected on floor 6
Bright, heat-insulating shield 5 may also be configured to other quantity with the groove 10 connected on floor 6, just not repeat one by one herein.
The plug cone 4 is made up of high temperature ablation resistant material, reduces serious ablation of the high-temperature fuel gas to plug cone 4.
The ring laryngeal mask 1 is made up of high temperature ablation resistant material, it is ensured that during work, will not be caused due to the expanded by heating of material
Area between ring laryngeal mask 1 and plug cone 4 becomes big, and then influences nozzle performance.
Preferably, sealing ring is installed between the step 2 32 of the port of export of the ring laryngeal mask 1 and the jet pipe housing 3
15。
The sealing that sealing ring 15 is used between ring laryngeal mask 1 and jet pipe housing 3, the material of sealing ring 15 is typically from resistant to elevated temperatures
The soft graphite or red copper of encapsulant, such as sealing.
Preferably, the jet pipe housing 3 is provided with unthreaded hole 21, and jet pipe housing 3 passes through unthreaded hole 21 and engine after-burner
Housing is connected.
The quantity of unthreaded hole 21 on jet pipe housing 3 is eight.
Need explanation but, the quantity of the unthreaded hole 21 on jet pipe housing 3 is only intended to for example, jet pipe shell for eight
Unthreaded hole 21 on body 3 may also be configured to other quantity, just not repeat one by one herein.
Unthreaded hole 21 on jet pipe housing 3 is arranged on jet pipe housing 3 by center of circle annular of the axis of jet pipe housing 3.
Preferably, jet pipe housing 3 is provided with groove 16, and the groove 16 is used for the tongue pair with after-burner shell flange
Should, for sealing.
Preferably, the floor 6 is structure as a whole with the boss 7.
The solid-liquid rocket circular seam type plug nozzle that the present invention is provided, has the following advantages that：
High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enter via the arrival end of jet pipe housing 3, and combustion gas exists
Converging portion 8 is ramped up, and is reached in the throat of ring laryngeal mask 1 and expansion segment 9 is flowed into after velocity of sound and is continued to accelerate to supersonic speed.
1st, suitable for the solid-liquid rocket of different operating height.
2nd, compact conformation, size is smaller, it is adaptable to the ground experiment of solid-liquid rocket.
3rd,, can be in very big working height range with automatic height compensation characteristic compared with traditional bell nozzle
Higher nozzle efficiency is kept, the wider solid-liquid rocket of working height range is particularly suitable for use in.
4th, nozzle entry plane can play a part of flow-disturbing, be conducive to the blending of combustion gas, improve solid-liquid rocket
Efficiency of combustion, improves engine performance.
5th, the actual divergence ratio of jet pipe can change with the change of engine chamber pressure, it is adaptable to the solid-liquid with change propulsive characteristic
Rocket engine.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
1. a kind of solid-liquid rocket circular seam type plug nozzle, it is characterised in that including ring laryngeal mask, jet pipe pressing plate, jet pipe shell
Body, plug cone and heat-insulating shield；
The ring laryngeal mask is arranged on the port of export of the jet pipe housing by the jet pipe pressing plate；
Boss is provided with by floor in the jet pipe housing；
The plug cone is suspended in the throat of the ring laryngeal mask and is connected with the boss；
The throat of the outer peripheral face and the ring laryngeal mask of the plug cone cooperatively forms converging portion and expansion segment；
The heat-insulating shield is arranged on the arrival end of the jet pipe housing, and the heat-insulating shield is logical provided with what is connected with the floor
Groove.
2. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the ring laryngeal mask
Throat includes hemispherical-shaped aperture and the through hole being sequentially connected, and the plug cone includes the arc section and conical section being sequentially connected, the circle
The end face of segmental arc is connected with the boss, and the outer peripheral face of the arc section is engaged to form converging portion with the hemispherical-shaped aperture, institute
The through hole that conical section stretches out the ring laryngeal mask is stated, the outer peripheral face of the conical section is engaged to form expansion segment with the through hole.
3. solid-liquid rocket circular seam type plug nozzle according to claim 2, it is characterised in that the circle of the plug cone
The end face of segmental arc is provided with groove, and the end face of the arc section of the plug cone is set on the boss and passed through by the groove
Bolt is connected as one with the boss.
4. solid-liquid rocket circular seam type plug nozzle according to claim 3, it is characterised in that set in the boss
Have and screwed hole is provided with bolt hole, the groove, the bolt is connected through the bolt hole with the screwed hole.
5. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the heat-insulating shield with
The jet pipe housing is to be detachably connected.
6. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the jet pipe pressing plate
It is to be detachably connected with the jet pipe housing.
7. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that it is described state plug cone by
High temperature ablation resistant material is made.
8. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the ring laryngeal mask by
High temperature ablation resistant material is made.
9. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the ring laryngeal mask with
Sealing ring is installed between the port of export of the jet pipe housing.
10. solid-liquid rocket circular seam type plug nozzle according to claim 1, it is characterised in that the floor with
The boss is structure as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710616678.6A CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710616678.6A CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107165739A true CN107165739A (en) | 2017-09-15 |
| CN107165739B CN107165739B (en) | 2019-03-22 |
Family
ID=59817511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710616678.6A Active CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107165739B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| RU2737821C1 (en) * | 2020-06-09 | 2020-12-04 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Dropping together with part of pyro drive a nozzle plug of engine, located inside fuselage of unmanned aerial vehicle |
| CN114776481A (en) * | 2022-04-26 | 2022-07-22 | 北京理工大学 | Plug type spray pipe engine with secondary flow injection structure |
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| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
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| US20160123178A1 (en) * | 2013-05-31 | 2016-05-05 | General Electric Company | Dual-mode plug nozzle |
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| CN106930866A (en) * | 2017-01-26 | 2017-07-07 | 北京航空航天大学 | A kind of solid-liquid rocket ground experiment jet pipe blocking cover structure |
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| US3144751A (en) * | 1961-05-10 | 1964-08-18 | United Aircraft Corp | Hybrid rocket |
| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
| CN102635463A (en) * | 2012-04-05 | 2012-08-15 | 北京航空航天大学 | Cold-flow test device for one-unit linear plug spray pipe |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139296A (en) * | 2018-09-11 | 2019-01-04 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| CN109139296B (en) * | 2018-09-11 | 2020-01-24 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| RU2737821C1 (en) * | 2020-06-09 | 2020-12-04 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Dropping together with part of pyro drive a nozzle plug of engine, located inside fuselage of unmanned aerial vehicle |
| CN114776481A (en) * | 2022-04-26 | 2022-07-22 | 北京理工大学 | Plug type spray pipe engine with secondary flow injection structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107165739B (en) | 2019-03-22 |
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